Airworthiness Directives; The Boeing Company Model 747 Airplanes, 32064-32069 [2012-13187]
Download as PDF
<![CDATA[
32064
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(m) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2011–0155, dated August 25, 2011,
and the following service information, for
related information.
(i) Airbus A318/A319/A320/A321 ALS Part
5—Fuel Airworthiness Limitations, dated
February 28, 2006.
(ii) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19,
2005.
(iii) A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 2, dated July 8, 2008.
(iv) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 4, dated August 26, 2010.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; Internet
https://www.airbus.com. You may review
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on May 18,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–13191 Filed 5–30–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
mstockstill on DSK4VPTVN1PROD with PROPOSALS
14 CFR Part 39
[Docket No. FAA–2012–0492; Directorate
Identifier 2010–NM–126–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain The Boeing
Company Model 747 airplanes. The
existing AD currently requires repetitive
visual inspections around the bushings
of the wing landing gear (WLG) beam
outboard end fittings for corrosion, and
rework if necessary; and ultrasonic
inspections for cracks of the outboard
end fittings of the WLG support beams,
and rework if necessary. Since we
issued that AD, there have been new
reports of corrosion damage to the end
fittings of the WLG support beams, and
one report of subsequent cracking in the
end fittings. This proposed AD would
add airplanes and repetitive inspections
of the outboard end fitting of the left
and right WLG support beams for cracks
and corrosion, and corrective actions if
necessary. We are proposing this AD to
detect and correct corrosion and
subsequent cracking in the outboard end
fittings, which could result in
separation of the fitting and damage to
adjacent flight control cables and
hydraulic systems and consequent
reduced controllability of the airplane.
DATES: We must receive comments on
this proposed AD by July 16, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1, fax 206–766–5680; email
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
SUMMARY:
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington
98057–3356; phone: (425) 917–6432;
fax: (425) 917–6590; email:
bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0492; Directorate Identifier
2010–NM–126–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On July 7, 1989, we issued AD 89–15–
07, amendment 39–6267 (54 FR 30009,
July 18, 1989), for certain Model 747
airplanes. That AD requires visual
inspections around the bushings of the
wing landing gear for corrosion, and
repair if necessary, and ultrasonic
inspections for cracks of the outboard
end fittings of the WLG support beams,
and overhaul if necessary. That AD
resulted from a report of a fracture of the
outboard end fitting of a left WLG beam.
We issued that AD to prevent failure of
the outboard end fitting of a WLG beam
with possible damage to control cables
or hydraulic lines in the area of the
landing gear beam.
E:\FR\FM\31MYP1.SGM
31MYP1
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
Actions Since Existing AD Was Issued
Since we issued AD 89–15–07,
amendment 39–6267 (54 FR 30009, July
18, 1989), we have received new reports
of corrosion damage to the end fittings
of the WLG support beams, and one
report of subsequent cracking in the end
fittings. The end fittings are installed on
the outboard ends of the WLG support
beams, and they attach to gate fittings
installed on the rear wing spars. There
are two types of end fittings used—one
is a two-piece end fitting installed in a
‘‘back to back’’ configuration; the other
is a one-piece end fitting.
Boeing Service Bulletin 747–57–2244,
Revision 1, dated July 28, 1988, was
referred to in the existing AD for
accomplishing the required actions on
Model 747 airplanes having line
numbers 1 through 695. The terminating
action specified in that service bulletin
involves replacing each of the end
fitting lug bore and bolt hole bushings
with new standard or oversize bushings
which are installed with sealant to
provide better corrosion prevention.
That terminating action was
incorporated into the design of
replacement fittings used on production
airplanes having line numbers 696 and
subsequent.
Although the terminating action
seemed to work well on airplanes
having line numbers 1 through 695,
recent reports from operators of
airplanes having line numbers 696 and
subsequent revealed that the problem
occurred again. Further investigation
revealed that the corrosion started at the
lug bore and bushing interface because
moisture continued to develop in that
area due to exposure of the end fittings
to environmental conditions.
Subsequently, cracks have occurred at
the corroded areas of the end fittings;
therefore, the terminating action in that
service bulletin is no longer valid
because the unsafe condition specified
in the existing AD has not been
corrected.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Relevant Service Information
Since the issuance of AD 89–15–07,
amendment 39–6267 (54 FR 30009, July
18, 1989), Boeing has issued Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. This new service
information is applicable to Model 747
airplanes having line numbers 1 through
1419 inclusive, which includes
airplanes on which the terminating
action in AD 89–15–07 was done.
We have reviewed Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. This service
bulletin describes procedures for
repetitive detailed and ultrasonic
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
inspections, as applicable, for cracks
and corrosion of the end fittings of the
left and right WLG support beams; and
repetitive detailed inspections of the
fillet seal for damage, as applicable. The
service information describes necessary
actions and options after accomplishing
the inspections, depending on the
findings and configurations. Those
actions and options (including Options
1A and 1B) include the following:
• Repairing or changing each end
fitting (by installing higher interference
fit bushings on the end fitting), which
is identified as ‘‘Part 7’’ of this service
bulletin, may be done in lieu of the
inspections described previously, but is
necessary for findings of cracks or
corrosion.
• Repetitively inspecting, as
described previously, along with an
additional inspection of the fillet seal
for damage; and applying corrosion
inhibiting compound or doing ‘‘Part 7’’
of this service bulletin, if necessary.
• Doing ‘‘Post-Part 7 inspections,’’
which involves actions similar to the
inspections for cracks, corrosion, and
damage described previously.
The recommended compliance times
follow:
• Detailed and ultrasonic inspections:
The initial compliance time for these
inspections depends on configuration,
and is either (1) 8 years on the end
fitting and 18 months after the date on
this service bulletin (whichever is later);
or (2) 10 years on the end fitting and 24
months after the date on this service
bulletin (whichever is later). The
repetitive interval also depends on
configurations and findings, and ranges
between 12 and 24 months.
• ‘‘Part 7’’ of this service bulletin: The
initial compliance time is the later of
20,000 total flight cycles on an end
fitting, and either 18 or 24 months
(depending on configuration). The
repetitive interval is either 13,000 or
16,000 flight cycles on an end fitting;
depending on configuration.
• ‘‘Post-Part 7’’ inspections: The
compliance time is 12 years after the
repair or change. The subsequent
repetitive intervals range between 12
months and 36 months, depending on
findings and configurations.
For airplanes on which any crack,
corrosion, or damage is found, the
compliance time for ‘‘Part 7’’ or
application of corrosion inhibitor is
before further flight.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
PO 00000
Frm 00028
Fmt 4702
Sfmt 4702
32065
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would retain
certain requirements of the existing AD.
This proposed AD would also add
airplanes and require accomplishing the
actions specified in the service
information described previously.
Changes to Existing AD
We have changed the applicability of
AD 89–15–07, amendment 39–6267 (54
FR 30009, July 18, 1989), in this
proposed AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models. We have also changed
the legal name of the manufacturer as
published in the most recent type
certificate data sheet for the affected
airplane models.
This proposed AD would retain
certain requirements of AD 89–15–07,
amendment 39–6267 (54 FR 30009, July
18, 1989). Since AD 89–15–07 was
issued, the AD format has been revised,
and certain paragraphs have been
rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
89–15–07, Amendment 39–6267 (54 FR
30009, July 18, 1989)
paragraph
paragraph
paragraph
paragraph
A
B
C
D
Corresponding
requirement in this
proposed AD
paragraph (g)
paragraph (g)(1)
paragraph (g)(2)
paragraph (g)(3)
In addition, we have revised
paragraph (g)(3) of this proposed AD
(which was designated as paragraph D.
in the existing AD) to require that if any
corrosion is found after the effective
date of this proposed AD, rework is
required before further flight. We have
reduced the compliance time to do the
rework from ‘‘within 12 months’’ to
‘‘before further flight’’ because extensive
service history has shown that the
deferral of known airplane damage such
as cracks and corrosion has not
provided an acceptable level of safety.
Service history has shown that the
extent of damage from unrepaired
corrosion can not reliably be determined
by inspection techniques. The damaged
corroded material must first be removed
and only then can the remaining
material dimensions be accurately
compared to the allowable damage
limits. The extent of unrepaired
corrosion damage can not be accurately
E:\FR\FM\31MYP1.SGM
31MYP1
32066
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
determined by current inspection
methods. Further, the reliance for
operation with known damage is
predicated on the adjacent and
associated structure being free from
other damage during this time period,
which has not been demonstrated by
older airplanes.
Depending on airplane configuration,
the new proposed inspections would
take between 1 and 4 work hours per
airplane, at an average labor rate of $85
per work hour. Based on these figures,
the estimated cost of the new
in the Accomplishment Instructions of
this service bulletin specify both
detailed and high frequency eddy
current (HFEC) inspections. We have
confirmed with Boeing that its intent is
that this service bulletin specify only a
detailed inspection for those conditions.
inspections specified in this proposed
AD for U.S. operators is between
$14,705 and $58,820, or between $85
and $340 per airplane, per inspection
cycle.
Difference Between the Proposed AD
and the Service Information
Operators should note that Conditions
6, 13, and 16 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–57A2331, dated November
12, 2009, specify a detailed inspection.
However, the corresponding conditions
Costs of Compliance
We estimate that this proposed AD
affects 173 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Inspections [retained actions
from existing AD 89–15–07,
amendment 39–6267 (54 FR
30009, July 18, 1989)].
Inspections [new proposed action].
10 work-hours × $85 per hour
= $850 per inspection cycle.
$0
$850 per inspection cycle ........
$147,050 per inspection
cycle.
Up to 67 work-hours × $85 per
hour = $5,695 per inspection
cycle, depending on configuration.
0
Up to $5,695 per inspection
cycle, depending on configuration.
Up to $985,235 per inspection cycle, depending on
configuration.
We estimate the following costs to do
any necessary repairs/replacements that
would be required based on the results
Parts cost
Cost on U.S.
operators
Action
of the proposed inspection. We have no
way of determining the number of
aircraft that might need these repairs/
replacements:
ON-CONDITION COSTS
Labor cost
Parts cost
Repair or replacement ........
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Action
Up to 71 work-hours × $85 per hour = $6,035, depending on configuration.
Up to $26,436, depending
on configuration.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
List of Subjects in 14 CFR Part 39
PO 00000
Frm 00029
Fmt 4702
Sfmt 4702
Cost per product
Up to $32,471, depending
on configuration.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
89–15–07, Amendment 39–6267 (54 FR
30009, July 18, 1989), and adding the
following new AD:
The Boeing Company: Docket No. FAA–
2012–0492; Directorate Identifier 2010–
NM–126–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by July 16, 2012.
E:\FR\FM\31MYP1.SGM
31MYP1
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
(b) Affected ADs
This AD supersedes AD 89–15–07,
Amendment 39–6267 (54 FR 30009, July 18,
1989).
(c) Applicability
This AD applies to The Boeing Company
Model 747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, 747SR, and
747SP series airplanes; certificated in any
category; as identified in Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by new reports of
corrosion damage to the end fittings of the
wing landing gear (WLG) support beams, and
one report of subsequent cracking in the end
fittings. We are issuing this AD to detect and
correct corrosion and subsequent cracking in
the outboard end fittings, which could result
in separation of the fitting and damage to
adjacent flight control cables and hydraulic
systems and consequent reduced
controllability of the airplane.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Repetitive Inspections With
Revised Compliance Times
This paragraph restates the requirements of
paragraphs A., B., C., and D., of AD 89–15–
07, Amendment 39–6267 (54 FR 30009, July
18, 1989): For airplanes identified in Boeing
Service Bulletin 747–57–2244, Revision 1,
dated July 28, 1988: Prior to the
accumulation of 30,000 flight hours or 8
years in service, whichever occurs first; or
within the next 14 months after August 22,
1989 (the effective date of AD 89–15–07);
whichever occurs later; visually inspect
around the fitting lug bushings at the wing
landing gear (WLG) beam outboard end
fittings for corrosion, and ultrasonically
inspect the WLG beam outboard end fittings
for cracks, in accordance with Boeing Service
Bulletin 747–57–2244, Revision 1, dated July
28, 1988. Accomplishing the initial
inspections required by paragraph (j) of this
AD terminates the inspections required by
this paragraph.
(1) If no cracking or corrosion is found,
repeat the inspections at intervals not to
exceed 18 months until paragraph (j) of this
AD has been accomplished.
(2) If cracking is found, prior to further
flight, remove the WLG beam outboard
fitting, and rework, in accordance with
Boeing Service Bulletin 747–57–2244,
Revision 1, dated July 28, 1988.
(3) If only corrosion is found, within the
next 12 months, rework in accordance with
Boeing Service Bulletin 747–57–2244,
Revision 1, dated July 28, 1988. The
ultrasonic inspections for cracks required by
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
paragraph (g) of this AD must be
accomplished at intervals not to exceed 6
months until the rework is accomplished. For
any corrosion that is found after the effective
date of this AD, the rework must be done
before further flight.
(h) Retained Terminating Action
This paragraph restates the requirements of
paragraph E., of AD 89–15–07, Amendment
39–6267 (54 FR 30009, July 18, 1989):
Terminating action for the inspections
required by paragraph (g) of this AD consists
of rework of the WLG beam outboard fittings,
in accordance with Boeing Service Bulletin
747–57–2244, Revision 1, dated July 28,
1988.
(i) New Compliance Times for This AD
For all the actions identified in paragraphs
(j) through (t) of this AD, do the actions at
the applicable time specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–57A2331, dated November 12,
2009. Where paragraph 1.E., ‘‘Compliance’’ of
this service bulletin specifies a compliance
time relative to the original issue date of the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(j) New Repetitive Inspections for Groups 1
Through 5 Airplanes
For Groups 1 through 3 airplanes,
Configurations 1 and 2; and Groups 4 and 5
airplanes: Do detailed and ultrasonic
inspections of the end fittings for cracks and
corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(k) New Inspections for No Crack or
Corrosion Findings for Groups 1 Through 5
Airplanes
If no crack or corrosion is found during any
inspection required by paragraph (j) of this
AD, do either of the actions required by
paragraph (k)(1) or (k)(2) of this AD.
(1) Repeat the detailed and ultrasonic
inspections of the end fittings for cracks and
corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(2) Do a detailed inspection of the end
fittings for fillet seal damage and for cracks
and corrosion, in accordance with Part 2 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the inspection
required by paragraph (k)(2) of this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (l) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
PO 00000
Frm 00030
Fmt 4702
Sfmt 4702
32067
fitting, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and thereafter repeat the
inspections required by paragraph
(k)(2)(ii)(B) of this AD.
(2) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (l) of this AD.
(l) New Repair for Crack or Corrosion
Findings for Groups 1 Through 5 Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (j) or
(k) of this AD: Repair or change the end
fitting, in accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. After accomplishing the
repair or change in accordance with Part 7 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraph (j) of this AD.
(m) New Repetitive Inspections and
Corrective Actions for Group 6 Airplanes
For Group 6 airplanes: Do a detailed
inspection of the end fittings for fillet seal
damage and for cracks and corrosion, in
accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(1) If no fillet seal damage, crack, or
corrosion is found: Do the detailed
inspection of the end fittings for fillet seal
damage and for cracks and corrosion, in
accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the detailed
inspection required by paragraph (m)(1) of
this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
E:\FR\FM\31MYP1.SGM
31MYP1
32068
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(2) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and thereafter repeat the
inspections required by paragraph
(m)(1)(ii)(B) of this AD.
(2) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(ii) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and thereafter repeat the
inspections required by paragraph (m)(2)(ii)
of this AD.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(n) New Repair for Group 6 Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (m) of
this AD: Repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. After accomplishing the
repair or change in accordance with Part 7 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraph (m) of this AD.
(o) New Optional Terminating Action for
Part 1, Part 2, and Part 3 Inspections
In lieu of doing Part 1, Part 2, or Part 3
inspections required by this AD: Repair or
change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009. After
accomplishing the repair or change in
accordance with Part 7 of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraphs (p) and (r) of this AD.
Doing the repair or change terminates the
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
Part 1, 2, or 3 inspections for that part only
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(p) New Follow-On End Fitting Inspection
for Groups 1 Through 5 Airplanes
For Groups 1 through 5 airplanes on which
the repair or change specified in Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, has been done: Do
detailed and ultrasonic inspections of the
end fittings for cracks and corrosion, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. If no crack or corrosion
is found, do the actions required by either
paragraph (p)(1) or (p)(2) of this AD.
(1) Repeat the detailed and ultrasonic
inspections of the end fittings for cracks and
corrosion required by paragraph (p) of this
AD.
(2) Do a detailed inspection of each end
fitting for fillet seal damage, cracks, and
corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the inspection
required by paragraph (p)(2) of this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (q) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (q) of this AD.
(2) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(q) New Repair for Groups 1 Through 5
Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (p) of
this AD: Repair or change the end fitting, in
accordance with Part 7 of the
PO 00000
Frm 00031
Fmt 4702
Sfmt 4702
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. After accomplishing the
repair or change in accordance with Part 7 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraphs (p) of this AD.
(r) New Follow-On End Fitting Inspection for
Group 6 Airplanes
For Group 6 airplanes on which the repair
or change specified in Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, has been done: Do a
detailed inspection of the end fittings for
fillet seal damage, cracks, and corrosion, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(1) If no fillet seal damage, crack, or
corrosion is found: Do a detailed inspection
of each end fitting for fillet seal damage,
cracks, and corrosion, in accordance with
Part 5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the inspection
required by paragraph (r)(1) of this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Do detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting as required
by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(2) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(2) If any fillet seal damage is found, but
no crack or corrosion is found: Do detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
4 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
E:\FR\FM\31MYP1.SGM
31MYP1
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
(i) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (s) of this AD.
(ii) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(s) New Repair for Group 6 Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (r) of
this AD: Repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(t) New Optional Action for Part 4, Part 5,
and Part 6 Inspections
In lieu of doing Part 4, Part 5, or Part 6
inspections required by this AD: Repair or
change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009. After
accomplishing the repair or change in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraphs (p) and (r) of this AD.
(u) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 89–15–07,
Amendment 39–6267 (54 FR 30009, July 18,
1989), are approved as AMOCs for the
corresponding requirements of this AD.
32069
of the wear indicating pins of all brake
assemblies, shortening the pin if the
wear indicating pin is too long,
inspecting for normal brake wear, and
replacing brakes with new brakes if
necessary. We are proposing this AD to
detect and correct improperly-sized
wear indicating pins, which, if not
corrected, could result in worn-out
brake pads and subsequent loss of
(v) Related Information
braking power, which could result in
(1) For more information about this AD,
runway overruns.
contact Bill Ashforth, Aerospace Engineer,
DATES: We must receive comments on
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
this proposed AD by July 16, 2012.
Avenue SW., Renton, Washington 98057–
ADDRESSES: You may send comments by
3356; phone: (425) 917–6432; fax: (425) 917–
any of the following methods:
6590; email: bill.ashforth@faa.gov.
• Federal eRulemaking Portal: Go to
(2) For service information identified in
https://www.regulations.gov. Follow the
this AD, contact Boeing Commercial
instructions for submitting comments.
Airplanes, Attention: Data & Services
• Fax: (202) 493–2251.
Management, P.O. Box 3707, MC 2H–65,
• Mail: U.S. Department of
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
Transportation, Docket Operations,
5680; email me.boecom@boeing.com; Internet M–30, West Building Ground Floor,
https://www.myboeingfleet.com. You may
Room W12–140, 1200 New Jersey
review copies of the referenced service
Avenue SE., Washington, DC 20590.
information at the FAA, Transport Airplane
• Hand Delivery: U.S. Department of
Directorate, 1601 Lind Avenue SW., Renton,
Transportation, Docket Operations,
Washington. For information on the
M–30, West Building Ground Floor,
availability of this material at the FAA, call
Room W12–140, 1200 New Jersey
425–227–1221.
Avenue SE., Washington, DC between 9
Issued in Renton, Washington, on May 18,
a.m. and 5 p.m., Monday through
2012.
Friday, except Federal holidays.
Michael Kaszycki,
For service information identified in
Acting Manager, Transport Airplane
this proposed AD, contact Gulfstream
Directorate, Aircraft Certification Service.
Aerospace Corporation, P.O. Box 2206,
[FR Doc. 2012–13187 Filed 5–30–12; 8:45 am]
Mail Station D–25, Savannah, Georgia
BILLING CODE 4910–13–P
31402–2206; telephone 800–810–4853;
fax 912–965–3520; email
DEPARTMENT OF TRANSPORTATION pubs@gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm. You
Federal Aviation Administration
may review copies of the referenced
service information at the FAA,
14 CFR Part 39
Transport Airplane Directorate, 1601
[Docket No. FAA–2012–0495; Directorate
Lind Avenue SW., Renton, Washington.
Identifier 2011–NM–236–AD]
For information on the availability of
RIN 2120–AA64
this material at the FAA, call 425–227–
1221.
Airworthiness Directives; Gulfstream
Examining the AD Docket
Aerospace LP (Type Certificate
Previously Held by Israel Aircraft
You may examine the AD docket on
Industries, Ltd.) Airplanes
the Internet at https://
www.regulations.gov; or in person at the
AGENCY: Federal Aviation
Docket Operations office between 9 a.m.
Administration (FAA), DOT.
and 5 p.m., Monday through Friday,
ACTION: Notice of proposed rulemaking
except Federal holidays. The AD docket
(NPRM).
contains this proposed AD, the
regulatory evaluation, any comments
SUMMARY: We propose to adopt a new
received, and other information. The
airworthiness directive (AD) for certain
street address for the Docket Operations
Gulfstream Aerospace LP (Type
office (telephone (800) 647–5527) is in
Certificate previously held by Israel
the ADDRESSES section. Comments will
Aircraft Industries, Ltd.) Model Galaxy
be available in the AD docket shortly
and Gulfstream 200 airplanes. This
after receipt.
proposed AD was prompted by reports
of degraded brake performance during
FOR FURTHER INFORMATION CONTACT: Tom
landing due to improperly-sized wear
Groves, Aerospace Engineer,
indicating pins. This proposed AD
International Branch, ANM–116,
would require determining the lengths
Transport Airplane Directorate, FAA,
PO 00000
Frm 00032
Fmt 4702
Sfmt 4702
E:\FR\FM\31MYP1.SGM
31MYP1
]]>Agencies
[Federal Register Volume 77, Number 105 (Thursday, May 31, 2012)]
[Proposed Rules]
[Pages 32064-32069]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-13187]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0492; Directorate Identifier 2010-NM-126-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 747 airplanes.
The existing AD currently requires repetitive visual inspections around
the bushings of the wing landing gear (WLG) beam outboard end fittings
for corrosion, and rework if necessary; and ultrasonic inspections for
cracks of the outboard end fittings of the WLG support beams, and
rework if necessary. Since we issued that AD, there have been new
reports of corrosion damage to the end fittings of the WLG support
beams, and one report of subsequent cracking in the end fittings. This
proposed AD would add airplanes and repetitive inspections of the
outboard end fitting of the left and right WLG support beams for cracks
and corrosion, and corrective actions if necessary. We are proposing
this AD to detect and correct corrosion and subsequent cracking in the
outboard end fittings, which could result in separation of the fitting
and damage to adjacent flight control cables and hydraulic systems and
consequent reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by July 16, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1, fax 206-766-5680; email me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6432; fax: (425) 917-6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0492;
Directorate Identifier 2010-NM-126-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On July 7, 1989, we issued AD 89-15-07, amendment 39-6267 (54 FR
30009, July 18, 1989), for certain Model 747 airplanes. That AD
requires visual inspections around the bushings of the wing landing
gear for corrosion, and repair if necessary, and ultrasonic inspections
for cracks of the outboard end fittings of the WLG support beams, and
overhaul if necessary. That AD resulted from a report of a fracture of
the outboard end fitting of a left WLG beam. We issued that AD to
prevent failure of the outboard end fitting of a WLG beam with possible
damage to control cables or hydraulic lines in the area of the landing
gear beam.
[[Page 32065]]
Actions Since Existing AD Was Issued
Since we issued AD 89-15-07, amendment 39-6267 (54 FR 30009, July
18, 1989), we have received new reports of corrosion damage to the end
fittings of the WLG support beams, and one report of subsequent
cracking in the end fittings. The end fittings are installed on the
outboard ends of the WLG support beams, and they attach to gate
fittings installed on the rear wing spars. There are two types of end
fittings used--one is a two-piece end fitting installed in a ``back to
back'' configuration; the other is a one-piece end fitting.
Boeing Service Bulletin 747-57-2244, Revision 1, dated July 28,
1988, was referred to in the existing AD for accomplishing the required
actions on Model 747 airplanes having line numbers 1 through 695. The
terminating action specified in that service bulletin involves
replacing each of the end fitting lug bore and bolt hole bushings with
new standard or oversize bushings which are installed with sealant to
provide better corrosion prevention. That terminating action was
incorporated into the design of replacement fittings used on production
airplanes having line numbers 696 and subsequent.
Although the terminating action seemed to work well on airplanes
having line numbers 1 through 695, recent reports from operators of
airplanes having line numbers 696 and subsequent revealed that the
problem occurred again. Further investigation revealed that the
corrosion started at the lug bore and bushing interface because
moisture continued to develop in that area due to exposure of the end
fittings to environmental conditions. Subsequently, cracks have
occurred at the corroded areas of the end fittings; therefore, the
terminating action in that service bulletin is no longer valid because
the unsafe condition specified in the existing AD has not been
corrected.
Relevant Service Information
Since the issuance of AD 89-15-07, amendment 39-6267 (54 FR 30009,
July 18, 1989), Boeing has issued Alert Service Bulletin 747-57A2331,
dated November 12, 2009. This new service information is applicable to
Model 747 airplanes having line numbers 1 through 1419 inclusive, which
includes airplanes on which the terminating action in AD 89-15-07 was
done.
We have reviewed Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009. This service bulletin describes procedures for
repetitive detailed and ultrasonic inspections, as applicable, for
cracks and corrosion of the end fittings of the left and right WLG
support beams; and repetitive detailed inspections of the fillet seal
for damage, as applicable. The service information describes necessary
actions and options after accomplishing the inspections, depending on
the findings and configurations. Those actions and options (including
Options 1A and 1B) include the following:
Repairing or changing each end fitting (by installing
higher interference fit bushings on the end fitting), which is
identified as ``Part 7'' of this service bulletin, may be done in lieu
of the inspections described previously, but is necessary for findings
of cracks or corrosion.
Repetitively inspecting, as described previously, along
with an additional inspection of the fillet seal for damage; and
applying corrosion inhibiting compound or doing ``Part 7'' of this
service bulletin, if necessary.
Doing ``Post-Part 7 inspections,'' which involves actions
similar to the inspections for cracks, corrosion, and damage described
previously.
The recommended compliance times follow:
Detailed and ultrasonic inspections: The initial
compliance time for these inspections depends on configuration, and is
either (1) 8 years on the end fitting and 18 months after the date on
this service bulletin (whichever is later); or (2) 10 years on the end
fitting and 24 months after the date on this service bulletin
(whichever is later). The repetitive interval also depends on
configurations and findings, and ranges between 12 and 24 months.
``Part 7'' of this service bulletin: The initial
compliance time is the later of 20,000 total flight cycles on an end
fitting, and either 18 or 24 months (depending on configuration). The
repetitive interval is either 13,000 or 16,000 flight cycles on an end
fitting; depending on configuration.
``Post-Part 7'' inspections: The compliance time is 12
years after the repair or change. The subsequent repetitive intervals
range between 12 months and 36 months, depending on findings and
configurations.
For airplanes on which any crack, corrosion, or damage is found,
the compliance time for ``Part 7'' or application of corrosion
inhibitor is before further flight.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain certain requirements of the existing
AD. This proposed AD would also add airplanes and require accomplishing
the actions specified in the service information described previously.
Changes to Existing AD
We have changed the applicability of AD 89-15-07, amendment 39-6267
(54 FR 30009, July 18, 1989), in this proposed AD to identify model
designations as published in the most recent type certificate data
sheet for the affected models. We have also changed the legal name of
the manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
This proposed AD would retain certain requirements of AD 89-15-07,
amendment 39-6267 (54 FR 30009, July 18, 1989). Since AD 89-15-07 was
issued, the AD format has been revised, and certain paragraphs have
been rearranged. As a result, the corresponding paragraph identifiers
have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in AD 89-15-07,
Amendment 39-6267 (54 FR 30009, Corresponding requirement in this
July 18, 1989) proposed AD
------------------------------------------------------------------------
paragraph A paragraph (g)
paragraph B paragraph (g)(1)
paragraph C paragraph (g)(2)
paragraph D paragraph (g)(3)
------------------------------------------------------------------------
In addition, we have revised paragraph (g)(3) of this proposed AD
(which was designated as paragraph D. in the existing AD) to require
that if any corrosion is found after the effective date of this
proposed AD, rework is required before further flight. We have reduced
the compliance time to do the rework from ``within 12 months'' to
``before further flight'' because extensive service history has shown
that the deferral of known airplane damage such as cracks and corrosion
has not provided an acceptable level of safety. Service history has
shown that the extent of damage from unrepaired corrosion can not
reliably be determined by inspection techniques. The damaged corroded
material must first be removed and only then can the remaining material
dimensions be accurately compared to the allowable damage limits. The
extent of unrepaired corrosion damage can not be accurately
[[Page 32066]]
determined by current inspection methods. Further, the reliance for
operation with known damage is predicated on the adjacent and
associated structure being free from other damage during this time
period, which has not been demonstrated by older airplanes.
Depending on airplane configuration, the new proposed inspections
would take between 1 and 4 work hours per airplane, at an average labor
rate of $85 per work hour. Based on these figures, the estimated cost
of the new inspections specified in this proposed AD for U.S. operators
is between $14,705 and $58,820, or between $85 and $340 per airplane,
per inspection cycle.
Difference Between the Proposed AD and the Service Information
Operators should note that Conditions 6, 13, and 16 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-57A2331,
dated November 12, 2009, specify a detailed inspection. However, the
corresponding conditions in the Accomplishment Instructions of this
service bulletin specify both detailed and high frequency eddy current
(HFEC) inspections. We have confirmed with Boeing that its intent is
that this service bulletin specify only a detailed inspection for those
conditions.
Costs of Compliance
We estimate that this proposed AD affects 173 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions 10 work-hours x $0 $850 per $147,050 per inspection cycle.
from existing AD 89-15-07, $85 per hour = inspection
amendment 39-6267 (54 FR $850 per cycle.
30009, July 18, 1989)]. inspection
cycle.
Inspections [new proposed Up to 67 work- 0 Up to $5,695 Up to $985,235 per inspection
action]. hours x $85 per per inspection cycle, depending on
hour = $5,695 cycle, configuration.
per inspection depending on
cycle, configuration.
depending on
configuration.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of
aircraft that might need these repairs/replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair or replacement.......... Up to 71 work-hours x Up to $26,436, Up to $32,471, depending on
$85 per hour = $6,035, depending on configuration.
depending on configuration.
configuration.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 1989), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0492; Directorate Identifier
2010-NM-126-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by July 16,
2012.
[[Page 32067]]
(b) Affected ADs
This AD supersedes AD 89-15-07, Amendment 39-6267 (54 FR 30009,
July 18, 1989).
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes; certificated in
any category; as identified in Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by new reports of corrosion damage to the
end fittings of the wing landing gear (WLG) support beams, and one
report of subsequent cracking in the end fittings. We are issuing
this AD to detect and correct corrosion and subsequent cracking in
the outboard end fittings, which could result in separation of the
fitting and damage to adjacent flight control cables and hydraulic
systems and consequent reduced controllability of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Repetitive Inspections With Revised Compliance Times
This paragraph restates the requirements of paragraphs A., B.,
C., and D., of AD 89-15-07, Amendment 39-6267 (54 FR 30009, July 18,
1989): For airplanes identified in Boeing Service Bulletin 747-57-
2244, Revision 1, dated July 28, 1988: Prior to the accumulation of
30,000 flight hours or 8 years in service, whichever occurs first;
or within the next 14 months after August 22, 1989 (the effective
date of AD 89-15-07); whichever occurs later; visually inspect
around the fitting lug bushings at the wing landing gear (WLG) beam
outboard end fittings for corrosion, and ultrasonically inspect the
WLG beam outboard end fittings for cracks, in accordance with Boeing
Service Bulletin 747-57-2244, Revision 1, dated July 28, 1988.
Accomplishing the initial inspections required by paragraph (j) of
this AD terminates the inspections required by this paragraph.
(1) If no cracking or corrosion is found, repeat the inspections
at intervals not to exceed 18 months until paragraph (j) of this AD
has been accomplished.
(2) If cracking is found, prior to further flight, remove the
WLG beam outboard fitting, and rework, in accordance with Boeing
Service Bulletin 747-57-2244, Revision 1, dated July 28, 1988.
(3) If only corrosion is found, within the next 12 months,
rework in accordance with Boeing Service Bulletin 747-57-2244,
Revision 1, dated July 28, 1988. The ultrasonic inspections for
cracks required by paragraph (g) of this AD must be accomplished at
intervals not to exceed 6 months until the rework is accomplished.
For any corrosion that is found after the effective date of this AD,
the rework must be done before further flight.
(h) Retained Terminating Action
This paragraph restates the requirements of paragraph E., of AD
89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 1989):
Terminating action for the inspections required by paragraph (g) of
this AD consists of rework of the WLG beam outboard fittings, in
accordance with Boeing Service Bulletin 747-57-2244, Revision 1,
dated July 28, 1988.
(i) New Compliance Times for This AD
For all the actions identified in paragraphs (j) through (t) of
this AD, do the actions at the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009. Where paragraph 1.E.,
``Compliance'' of this service bulletin specifies a compliance time
relative to the original issue date of the service bulletin, this AD
requires compliance within the specified compliance time after the
effective date of this AD.
(j) New Repetitive Inspections for Groups 1 Through 5 Airplanes
For Groups 1 through 3 airplanes, Configurations 1 and 2; and
Groups 4 and 5 airplanes: Do detailed and ultrasonic inspections of
the end fittings for cracks and corrosion, in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(k) New Inspections for No Crack or Corrosion Findings for Groups 1
Through 5 Airplanes
If no crack or corrosion is found during any inspection required
by paragraph (j) of this AD, do either of the actions required by
paragraph (k)(1) or (k)(2) of this AD.
(1) Repeat the detailed and ultrasonic inspections of the end
fittings for cracks and corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(2) Do a detailed inspection of the end fittings for fillet seal
damage and for cracks and corrosion, in accordance with Part 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the inspection required by paragraph (k)(2) of this AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (l) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 2
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 3
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009, and thereafter repeat the
inspections required by paragraph (k)(2)(ii)(B) of this AD.
(2) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (l) of this AD.
(l) New Repair for Crack or Corrosion Findings for Groups 1 Through 5
Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (j) or (k) of this AD: Repair or change the
end fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009. After accomplishing the repair or change in
accordance with Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the
applicable actions required by paragraph (j) of this AD.
(m) New Repetitive Inspections and Corrective Actions for Group 6
Airplanes
For Group 6 airplanes: Do a detailed inspection of the end
fittings for fillet seal damage and for cracks and corrosion, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If no fillet seal damage, crack, or corrosion is found: Do
the detailed inspection of the end fittings for fillet seal damage
and for cracks and corrosion, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the detailed inspection required by paragraph (m)(1) of this
AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 2
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part
[[Page 32068]]
3 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2331, dated November 12, 2009.
(1) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(2) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, and thereafter repeat the inspections required by
paragraph (m)(1)(ii)(B) of this AD.
(2) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(i) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(ii) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, and thereafter repeat the inspections required by
paragraph (m)(2)(ii) of this AD.
(n) New Repair for Group 6 Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (m) of this AD: Repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009. After accomplishing the repair or change in
accordance with Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the
applicable actions required by paragraph (m) of this AD.
(o) New Optional Terminating Action for Part 1, Part 2, and Part 3
Inspections
In lieu of doing Part 1, Part 2, or Part 3 inspections required
by this AD: Repair or change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2331, dated November 12, 2009. After accomplishing
the repair or change in accordance with Part 7 of Boeing Alert
Service Bulletin 747-57A2331, dated November 12, 2009, do the
applicable actions required by paragraphs (p) and (r) of this AD.
Doing the repair or change terminates the Part 1, 2, or 3
inspections for that part only of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(p) New Follow-On End Fitting Inspection for Groups 1 Through 5
Airplanes
For Groups 1 through 5 airplanes on which the repair or change
specified in Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, has
been done: Do detailed and ultrasonic inspections of the end
fittings for cracks and corrosion, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009. If no crack or corrosion is found,
do the actions required by either paragraph (p)(1) or (p)(2) of this
AD.
(1) Repeat the detailed and ultrasonic inspections of the end
fittings for cracks and corrosion required by paragraph (p) of this
AD.
(2) Do a detailed inspection of each end fitting for fillet seal
damage, cracks, and corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the inspection required by paragraph (p)(2) of this AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 5 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (q) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 5
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (q) of this AD.
(2) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009; and repeat the detailed and HFEC inspections of
each end fitting for cracks and corrosion, in accordance with Part 6
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(q) New Repair for Groups 1 Through 5 Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (p) of this AD: Repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009. After accomplishing the repair or change in
accordance with Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the
applicable actions required by paragraphs (p) of this AD.
(r) New Follow-On End Fitting Inspection for Group 6 Airplanes
For Group 6 airplanes on which the repair or change specified in
Part 7 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2331, dated November 12, 2009, has been done: Do a
detailed inspection of the end fittings for fillet seal damage,
cracks, and corrosion, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(1) If no fillet seal damage, crack, or corrosion is found: Do a
detailed inspection of each end fitting for fillet seal damage,
cracks, and corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the inspection required by paragraph (r)(1) of this AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Do detailed and HFEC inspections of each end
fitting for cracks and corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting as required by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 5
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and repeat the detailed and
HFEC inspections of each end fitting for cracks and corrosion, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009.
(2) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009; and repeat the detailed and HFEC inspections of
each end fitting for cracks and corrosion, in accordance with Part 6
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(2) If any fillet seal damage is found, but no crack or
corrosion is found: Do detailed and HFEC inspections of each end
fitting for cracks and corrosion, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
[[Page 32069]]
(i) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (s) of this AD.
(ii) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 4
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009; and repeat the detailed and HFEC inspections of
each end fitting for cracks and corrosion, in accordance with Part 6
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(s) New Repair for Group 6 Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (r) of this AD: Repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009.
(t) New Optional Action for Part 4, Part 5, and Part 6 Inspections
In lieu of doing Part 4, Part 5, or Part 6 inspections required
by this AD: Repair or change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2331, dated November 12, 2009. After accomplishing
the repair or change in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, do the applicable actions required by paragraphs
(p) and (r) of this AD.
(u) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 89-15-07, Amendment 39-6267 (54 FR
30009, July 18, 1989), are approved as AMOCs for the corresponding
requirements of this AD.
(v) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6432; fax: (425) 917-6590; email:
bill.ashforth@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1, fax 206-766-5680; email
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
Issued in Renton, Washington, on May 18, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-13187 Filed 5-30-12; 8:45 am]
BILLING CODE 4910-13-P
