Airworthiness Directives; The Boeing Company Model 767 Airplanes, 6154-6157 [2010-2685]
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Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules
Dated: January 31, 2010.
Edward J. DeMarco,
Acting Director, Federal Housing Finance
Agency.
[FR Doc. 2010–2677 Filed 2–5–10; 8:45 am]
BILLING CODE P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0033; Directorate
Identifier 2009–NM–099–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 767 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Model
767 airplanes. The existing AD currently
requires repetitive detailed and high
frequency eddy current (HFEC)
inspections of the station (STA) 1809.5
bulkhead for cracking, and corrective
actions if necessary. This proposed AD
would expand the inspection area to
include the vertical inner chord at STA
1809.5. This proposed AD results from
reported fatigue cracking in the vertical
inner chord and the forward outer chord
while doing the detailed inspection of
the horizontal inner chord at STA
1809.5. We are proposing this AD to
detect and correct fatigue cracking in
the bulkhead structure at STA 1809.5
and the vertical inner chord at STA
1809.5, which could result in failure of
the bulkhead structure for carrying the
flight loads of the horizontal stabilizer,
and consequent loss of controllability of
the airplane.
DATES: We must receive comments on
this proposed AD by March 25, 2010.
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.,
VerDate Nov<24>2008
11:50 Feb 05, 2010
Jkt 220001
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; e-mail
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 or 425–227–1152.
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:
Berhane Alazar, Airframe Branch,
ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057–3356;
telephone (425) 917–6577; fax (425)
917–6590.
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–2010–0033; Directorate Identifier
2009–NM–099–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.
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Discussion
On November 9, 2006, we issued AD
2006–24–04, Amendment 39–14833 (71
FR 68432, November 27, 2006), for all
Model 767 airplanes. That AD requires
repetitive detailed and high frequency
eddy current (HFEC) inspections of the
station (STA) 1809.5 bulkhead for
cracking, and corrective actions if
necessary. That AD resulted from
fatigue cracks found in the forward
outer chord and horizontal inner chord
at STA 1809.5. We issued that AD to
detect and correct cracking in the
bulkhead structure at STA 1809.5,
which could result in failure of the
bulkhead structure for carrying the
flight loads of the horizontal stabilizer,
and consequent loss of controllability of
the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2006–24–04, an
operator reported fatigue cracking in the
vertical inner chord found while doing
the detailed inspection of the horizontal
inner chord required by that AD. A
surface HFEC inspection was done to
confirm the crack. The crack was found
on the right side of the structure at a
fastener hole near buttock line (BL) 28.5,
water line (WL) 257, common to both
the horizontal and vertical inner chord.
The vertical inner chord crack was
found on an airplane with 28,234 total
flight cycles.
Relevant Service Information
AD 2006–24–04 refers to Boeing Alert
Service Bulletin 767–53A0131, dated
March 30, 2006, as the appropriate
source of service information for the
required actions. We have reviewed
Boeing Alert Service Bulletin 767–
53A0131, Revision 1, dated March 12,
2009. Revision 1 adds a surface HFEC
inspection for the vertical inner chord,
and clarifies the procedures for
inspecting the horizontal inner chord.
The service bulletin specifies a
compliance time of before 15,000 total
flight cycles or within 6,000 flight
cycles after the previous PARTS 1–4
inspection, whichever occurs first, for
the surface HFEC inspection for the
vertical inner chord. The service
bulletin also specifies a repeat interval
6,000 flight cycles thereafter for the
surface HFEC inspection for the vertical
inner chord.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 2006–
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Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules
24–04 and retain the requirements of the
existing AD. This proposed AD would
also require accomplishing the new
actions specified in the revised service
bulletin described previously.
Change to Paragraph (i) of the Existing
AD
We have revised paragraph (i) of the
existing AD to clarify that the
modification of a forward outer chord
may be done in accordance with Steps
4.A through 4.C and 4.G through 4.P of
Repair 9, dated April 15, 2006, of
Chapter 53–80–08 of the Boeing 767–
200 Structural Repair Manual (SRM),
Document D634T201; Boeing 767–300
SRM, Document D634T210; Boeing
767–300F SRM, Document D634T215;
or Boeing 767–400 SRM, Document
D634T225; as applicable. For a
horizontal inner chord, modification
may be done in accordance with Steps
4.A, 4.B, and 4.F through 4.P of Repair
10, dated April 15, 2006, of Chapter 53–
80–08 of the Boeing 767–200 SRM,
Document D634T201; Boeing 767–300
SRM, Document D634T210; Boeing
767–300F SRM, Document D634T215;
or Boeing 767–400 SRM, Document
D634T225; as applicable.
Change to Paragraph (j)(3) of the
Existing AD
Boeing Commercial Airplanes has
received an Organization Designation
Authorization (ODA), which replaces
their previous designation as a
Delegation Option Authorization (DOA)
holder. We have revised paragraph (j)(3)
of the existing AD (paragraph (n)(3) of
this AD) to delegate the authority to
approve an alternative method of
compliance for any repair required by
this AD to the Boeing Commercial
Airplanes ODA.
Costs of Compliance
There are about 975 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Repetitive inspections of STA 1805.5
(required by AD 2006–24–04).
Inspection of inner chord (new proposed
action).
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
Jkt 220001
Number of
U.S.-registered airplanes
Cost per airplane
$960 per inspection
cycle.
$160 per inspection
cycle.
$80
None ........
2
Regulatory Findings
We have 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 that the proposed regulation:
11:50 Feb 05, 2010
Parts
12
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.
VerDate Nov<24>2008
Average
labor rate
per hour
Work
hours
Action
$80
None ........
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); and
3. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
354
354
Fleet cost
$339,840 per inspection
cycle.
$56,640 per inspection
cycle.
68432, November 27, 2006) and adding
the following new AD:
The Boeing Company: Docket No. FAA–
2010–0033; Directorate Identifier 2009–
NM–099–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 25, 2010.
Affected ADs
(b) This AD supersedes AD 2006–24–04,
Amendment 39–14833.
Applicability
(c) This AD applies to all The Boeing
Company Model 767–200, –300, –300F, and
–400ER series airplanes, certificated in any
category.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Subject
The Proposed Amendment
Unsafe Condition
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(e) This AD results from reported fatigue
cracking in the vertical inner chord while
doing a detailed inspection of the horizontal
inner chord. The Federal Aviation
Administration is issuing this AD to detect
and correct fatigue cracking in the bulkhead
structure at station (STA) 1809.5 and the
vertical inner chord at STA 1809.5, which
could result in failure of the bulkhead
structure for carrying the flight loads of the
horizontal stabilizer, and consequent loss of
controllability of the airplane.
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]
Compliance
2. The FAA amends § 39.13 by
removing Amendment 39–14833 (71 FR
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(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Sfmt 4702
(f) You are responsible for having the
actions required by this AD performed within
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Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006–
24–04, With New Service Information
Repetitive Inspections and Corrective
Actions
(g) Before the accumulation of 15,000 total
flight cycles, or within 3,000 flight cycles
after January 2, 2007 (the effective date of AD
2006–24–04), whichever is later: Do the
detailed and high frequency eddy current
(HFEC) inspections for cracking as specified
in Parts 1, 2, 3, and 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–53A0131, dated March 30, 2006; or
Revision 1, dated March 12, 2009; and do all
corrective actions before further flight; by
accomplishing all the actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0131, dated March
30, 2006; or Boeing Alert Service Bulletin
767–53A0131, Revision 1, dated March 12,
2009; except as provided by paragraph (h) of
this AD. After the effective date of this AD,
use only Revision 1, dated March 12, 2009,
of Boeing Alert Service Bulletin 767–
53A0131. Repeat the inspections thereafter at
intervals not to exceed 6,000 flight cycles.
Accomplishing the corrective action for the
inspections specified in Part 1, 2, 3, or 4, as
applicable, of Boeing Alert Service Bulletin
767–53A0131, dated March 30, 2006; or
Revision 1, dated March 12, 2009; as
applicable; terminates the repetitive
inspections for that area only.
Exceptions to Service Bulletin
(h) If any cracking is found in the skin or
in any structure other than the forward outer
chord or horizontal inner chord during any
inspection required by paragraph (g) or (k) of
this AD, and Boeing Service Bulletin 767–
53A0131, dated March 30, 2006; or Boeing
Alert Service Bulletin 767–53A0131,
Revision 1, dated March 12, 2009; specifies
to contact Boeing for appropriate action:
Before further flight, repair the cracking
using a method approved in accordance with
the procedures specified in paragraph (n) of
this AD.
Optional Terminating Action for the
Repetitive Inspections Required by
Paragraph (g) of this AD
(i) If no cracking is found during the most
recent detailed and HFEC inspections for a
specified area as required by paragraph (g) of
this AD: Modification of a specified area in
accordance with a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA, terminates the repetitive
inspections required by paragraph (g) of this
AD for that area only. Modification of a
forward outer chord in accordance with
Steps 4.A through 4.C and 4.G through 4.P
of Repair 9, dated April 15, 2006, of Chapter
53–80–08 of the Boeing 767–200 Structural
Repair Manual (SRM), Document D634T201;
Boeing 767–300 SRM, Document D634T210;
Boeing 767–300F SRM, Document D634T215;
or Boeing 767–400 SRM, Document
D634T225; as applicable; also terminates the
repetitive inspections required by paragraph
(g) of this AD for that area. Modification of
a horizontal inner chord in accordance with
Steps 4.A, 4.B, and 4.F through 4.P of Repair
10, dated April 15, 2006, of Chapter 53–80–
08 of the Boeing 767–200 SRM, Document
D634T201; Boeing 767–300 SRM, Document
D634T210; Boeing 767–300F SRM, Document
D634T215; or Boeing 767–400 SRM,
Document D634T225; as applicable; also
terminates the repetitive inspections required
by paragraph (g) of this AD for that area.
Credit for Previously Accomplished Repairs
(j) Repair of a forward outer chord done
before January 2, 2007, in accordance with
Repair 9, dated April 15, 2006, of Chapter
53–80–08 of the Boeing 767–200 SRM,
Document D634T201; Boeing 767–300 SRM,
Document D634T210; Boeing 767–300F SRM,
Document D634T215; or Boeing 767–400
SRM, Document D634T225; as applicable; is
acceptable for compliance with the
requirements of paragraph (g) of this AD for
that area only. Repair of a horizontal inner
chord before January 2, 2007, in accordance
with Repair 10, dated April 15, 2006, of
Chapter 53–80–08 of the Boeing 767–200
SRM, Document D634T201; Boeing 767–300
SRM, Document D634T210; Boeing 767–300F
SRM, Document D634T215; or Boeing 767–
400 SRM, Document D634T225; as
applicable; is acceptable for compliance with
the requirements of paragraph (g) of this AD
for that area only.
New Requirements of This AD
Inspections
(k) At the later of the times specified in
paragraphs (k)(1) and (k)(2) of this AD, except
as specified in paragraph (l) of this AD: Do
the detailed and HFEC inspections for
cracking as specified in Parts 5 and 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0131, Revision 1,
dated March 12, 2009; and do all applicable
corrective actions by accomplishing all the
actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–53A0131, Revision 1, dated March 12,
2009; except as provided by paragraph (h) of
this AD. Do all applicable corrective actions
before further flight. Repeat the inspections
thereafter at intervals not to exceed 6,000
flight cycles. Accomplishing the corrective
action for the inspections specified in Part 5
or 6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 767–53A0131,
Revision 1, dated March 12, 2009, as
applicable, terminates the repetitive
inspections for that area only.
(1) 15,000 total flight cycles or 6,000 flight
cycles after the inspection required by
paragraph (g) of this AD, whichever occurs
first.
(2) 30 days after the effective date of this
AD.
Exceptions to the Service Bulletin
(l) Where Boeing Alert Service Bulletin
767–53A0131, Revision 1, dated March 12,
2009, specifies a compliance time ‘‘after the
date on the original issue of the service
bulletin’’ or ‘‘after the date on Revision 01 of
the service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
Optional Terminating Action for the
Repetitive Inspections Required by
Paragraph (k) of This AD
(m) If no cracking is found during the most
recent detailed and HFEC inspections for a
specified area as required by paragraph (k) of
this AD: Modification of a specified area in
accordance with a method approved by the
Manager, Seattle ACO, FAA, terminates the
repetitive inspections required by paragraph
(k) of this AD for that area only.
Note 1: Guidance on modifying a vertical
inner chord can be found in the service
information identified in Table 1 of this AD.
TABLE 1—SERVICE INFORMATION
Dated—
Of—
4.A through 4.C and 4.G through 4.Q of Repair 11 .............
August 15, 2008 ........
4.A through 4.C and 4.G through 4.Q of Repair 11 .............
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
Steps—
August 15, 2008 ........
4.A through 4.C and 4.G through 4.Q of Repair 11 .............
August 15, 2008 ........
4.A through 4.C and 4.G through 4.Q of Repair 11 .............
August 15, 2008 ........
Chapter 53-80–08 of the Boeing 767–200 SRM, Document
D634T201.
Chapter 53-80–08 of the Boeing 767–300 SRM, Document
D634T210.
Chapter 53-80–08 of the Boeing 767–300F SRM, Document D634T215.
Chapter 53-80–08 of the Boeing 767–400 SRM, Document
D634T225.
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11:50 Feb 05, 2010
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Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Berhane Alazar, Airframe Branch, ANM–
120S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
917–6577; fax (425) 917–6590. Or, e-mail
information to 9–ANM–Seattle–ACO–AMOC–
Requests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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 previously in
accordance with AD 2006–24–04 are
approved as AMOCs for the corresponding
provisions of this AD.
Issued in Renton, Washington, on January
28, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–2685 Filed 2–5–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0034; Directorate
Identifier 2009–NM–120–AD]
RIN 2120–AA64
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
Airworthiness Directives; Gulfstream
Aerospace LP Model Gulfstream 100
Airplanes, and Model Astra SPX and
1125 Westwind Astra Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed AD results from mandatory
continuing airworthiness information
SUMMARY:
VerDate Nov<24>2008
11:50 Feb 05, 2010
Jkt 220001
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as: Incomplete
closure of the MED [main entry door]
may be followed by in-flight opening of
the door. As a result, the MED and the
adjacent fuselage structure may be
damaged during opening and landing
impact. Damage to the left engine by
flying debris and objects may also occur.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by March 25, 2010.
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
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Gulfstream service information
identified in this proposed AD, contact
Gulfstream Aerospace Corporation, P.O.
Box 2206, Mail Station D–25, Savannah,
Georgia 31402–2206; telephone 800–
810–4853; fax 912–965–3520; e-mail
pubs@gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm. For
Honeywell service information
identified in this proposed AD, contact
Honeywell Aerospace, Technical
Publications and Distribution, M/S
2101–201, P.O. Box 52170, Phoenix,
Arizona 85072–2170; telephone 602–
365–5535; fax 602–365–5577; Internet
https://www.honeywell.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
or 425–227–1152.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
PO 00000
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6157
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
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:
Mike Borfitz, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2677; fax (425) 227–1149.
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–2010–0034; Directorate Identifier
2009–NM–120–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 based on those comments.
We have lengthened the 30-day
comment period for proposed ADs that
address MCAI originated by aviation
authorities of other countries to provide
adequate time for interested parties to
submit comments. The comment period
for these proposed ADs is now typically
45 days, which is consistent with the
comment period for domestic transport
ADs.
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 January 23, 2007, we issued AD
2007–03–05, Amendment 39–14916 (72
FR 4414, January 31, 2007). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2007–03–05, the
Civil Aviation Administration of Israel
(CAAI), which is the aviation authority
for Israel, has issued Israeli
Airworthiness Directive 31–06–11–05,
dated May 27, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
To increase pilots’ awareness to the
possibility of incomplete closure of the Main
Entry Door (MED) by the following means:
E:\FR\FM\08FEP1.SGM
08FEP1
]]>Agencies
[Federal Register Volume 75, Number 25 (Monday, February 8, 2010)]
[Proposed Rules]
[Pages 6154-6157]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-2685]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0033; Directorate Identifier 2009-NM-099-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 767 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Model 767 airplanes. The existing AD
currently requires repetitive detailed and high frequency eddy current
(HFEC) inspections of the station (STA) 1809.5 bulkhead for cracking,
and corrective actions if necessary. This proposed AD would expand the
inspection area to include the vertical inner chord at STA 1809.5. This
proposed AD results from reported fatigue cracking in the vertical
inner chord and the forward outer chord while doing the detailed
inspection of the horizontal inner chord at STA 1809.5. We are
proposing this AD to detect and correct fatigue cracking in the
bulkhead structure at STA 1809.5 and the vertical inner chord at STA
1809.5, which could result in failure of the bulkhead structure for
carrying the flight loads of the horizontal stabilizer, and consequent
loss of controllability of the airplane.
DATES: We must receive comments on this proposed AD by March 25, 2010.
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; e-mail 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 or
425-227-1152.
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: Berhane Alazar, Airframe Branch, ANM-
120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425)
917-6590.
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-2010-0033;
Directorate Identifier 2009-NM-099-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 November 9, 2006, we issued AD 2006-24-04, Amendment 39-14833
(71 FR 68432, November 27, 2006), for all Model 767 airplanes. That AD
requires repetitive detailed and high frequency eddy current (HFEC)
inspections of the station (STA) 1809.5 bulkhead for cracking, and
corrective actions if necessary. That AD resulted from fatigue cracks
found in the forward outer chord and horizontal inner chord at STA
1809.5. We issued that AD to detect and correct cracking in the
bulkhead structure at STA 1809.5, which could result in failure of the
bulkhead structure for carrying the flight loads of the horizontal
stabilizer, and consequent loss of controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2006-24-04, an operator reported fatigue
cracking in the vertical inner chord found while doing the detailed
inspection of the horizontal inner chord required by that AD. A surface
HFEC inspection was done to confirm the crack. The crack was found on
the right side of the structure at a fastener hole near buttock line
(BL) 28.5, water line (WL) 257, common to both the horizontal and
vertical inner chord. The vertical inner chord crack was found on an
airplane with 28,234 total flight cycles.
Relevant Service Information
AD 2006-24-04 refers to Boeing Alert Service Bulletin 767-53A0131,
dated March 30, 2006, as the appropriate source of service information
for the required actions. We have reviewed Boeing Alert Service
Bulletin 767-53A0131, Revision 1, dated March 12, 2009. Revision 1 adds
a surface HFEC inspection for the vertical inner chord, and clarifies
the procedures for inspecting the horizontal inner chord. The service
bulletin specifies a compliance time of before 15,000 total flight
cycles or within 6,000 flight cycles after the previous PARTS 1-4
inspection, whichever occurs first, for the surface HFEC inspection for
the vertical inner chord. The service bulletin also specifies a repeat
interval 6,000 flight cycles thereafter for the surface HFEC inspection
for the vertical inner chord.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2006-
[[Page 6155]]
24-04 and retain the requirements of the existing AD. This proposed AD
would also require accomplishing the new actions specified in the
revised service bulletin described previously.
Change to Paragraph (i) of the Existing AD
We have revised paragraph (i) of the existing AD to clarify that
the modification of a forward outer chord may be done in accordance
with Steps 4.A through 4.C and 4.G through 4.P of Repair 9, dated April
15, 2006, of Chapter 53-80-08 of the Boeing 767-200 Structural Repair
Manual (SRM), Document D634T201; Boeing 767-300 SRM, Document D634T210;
Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document
D634T225; as applicable. For a horizontal inner chord, modification may
be done in accordance with Steps 4.A, 4.B, and 4.F through 4.P of
Repair 10, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-
200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210;
Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document
D634T225; as applicable.
Change to Paragraph (j)(3) of the Existing AD
Boeing Commercial Airplanes has received an Organization
Designation Authorization (ODA), which replaces their previous
designation as a Delegation Option Authorization (DOA) holder. We have
revised paragraph (j)(3) of the existing AD (paragraph (n)(3) of this
AD) to delegate the authority to approve an alternative method of
compliance for any repair required by this AD to the Boeing Commercial
Airplanes ODA.
Costs of Compliance
There are about 975 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Work Average U.S.-
Action hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive inspections of STA 1805.5 12 $80 None................... $960 per inspection 354 $339,840 per inspection
(required by AD 2006-24-04). cycle. cycle.
Inspection of inner chord (new 2 $80 None................... $160 per inspection 354 $56,640 per inspection
proposed action). cycle. cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 have 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 that the 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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
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 Amendment 39-14833 (71 FR
68432, November 27, 2006) and adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0033; Directorate Identifier
2009-NM-099-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 25,
2010.
Affected ADs
(b) This AD supersedes AD 2006-24-04, Amendment 39-14833.
Applicability
(c) This AD applies to all The Boeing Company Model 767-200, -
300, -300F, and -400ER series airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reported fatigue cracking in the
vertical inner chord while doing a detailed inspection of the
horizontal inner chord. The Federal Aviation Administration is
issuing this AD to detect and correct fatigue cracking in the
bulkhead structure at station (STA) 1809.5 and the vertical inner
chord at STA 1809.5, which could result in failure of the bulkhead
structure for carrying the flight loads of the horizontal
stabilizer, and consequent loss of controllability of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within
[[Page 6156]]
the compliance times specified, unless the actions have already been
done.
Restatement of Requirements of AD 2006-24-04, With New Service
Information
Repetitive Inspections and Corrective Actions
(g) Before the accumulation of 15,000 total flight cycles, or
within 3,000 flight cycles after January 2, 2007 (the effective date
of AD 2006-24-04), whichever is later: Do the detailed and high
frequency eddy current (HFEC) inspections for cracking as specified
in Parts 1, 2, 3, and 4 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-53A0131, dated March 30, 2006; or
Revision 1, dated March 12, 2009; and do all corrective actions
before further flight; by accomplishing all the actions specified in
the Accomplishment Instructions of Boeing Alert Service Bulletin
767-53A0131, dated March 30, 2006; or Boeing Alert Service Bulletin
767-53A0131, Revision 1, dated March 12, 2009; except as provided by
paragraph (h) of this AD. After the effective date of this AD, use
only Revision 1, dated March 12, 2009, of Boeing Alert Service
Bulletin 767-53A0131. Repeat the inspections thereafter at intervals
not to exceed 6,000 flight cycles. Accomplishing the corrective
action for the inspections specified in Part 1, 2, 3, or 4, as
applicable, of Boeing Alert Service Bulletin 767-53A0131, dated
March 30, 2006; or Revision 1, dated March 12, 2009; as applicable;
terminates the repetitive inspections for that area only.
Exceptions to Service Bulletin
(h) If any cracking is found in the skin or in any structure
other than the forward outer chord or horizontal inner chord during
any inspection required by paragraph (g) or (k) of this AD, and
Boeing Service Bulletin 767-53A0131, dated March 30, 2006; or Boeing
Alert Service Bulletin 767-53A0131, Revision 1, dated March 12,
2009; specifies to contact Boeing for appropriate action: Before
further flight, repair the cracking using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD.
Optional Terminating Action for the Repetitive Inspections Required by
Paragraph (g) of this AD
(i) If no cracking is found during the most recent detailed and
HFEC inspections for a specified area as required by paragraph (g)
of this AD: Modification of a specified area in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA, terminates the repetitive inspections required by
paragraph (g) of this AD for that area only. Modification of a
forward outer chord in accordance with Steps 4.A through 4.C and 4.G
through 4.P of Repair 9, dated April 15, 2006, of Chapter 53-80-08
of the Boeing 767-200 Structural Repair Manual (SRM), Document
D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F
SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as
applicable; also terminates the repetitive inspections required by
paragraph (g) of this AD for that area. Modification of a horizontal
inner chord in accordance with Steps 4.A, 4.B, and 4.F through 4.P
of Repair 10, dated April 15, 2006, of Chapter 53-80-08 of the
Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document
D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400
SRM, Document D634T225; as applicable; also terminates the
repetitive inspections required by paragraph (g) of this AD for that
area.
Credit for Previously Accomplished Repairs
(j) Repair of a forward outer chord done before January 2, 2007,
in accordance with Repair 9, dated April 15, 2006, of Chapter 53-80-
08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM,
Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing
767-400 SRM, Document D634T225; as applicable; is acceptable for
compliance with the requirements of paragraph (g) of this AD for
that area only. Repair of a horizontal inner chord before January 2,
2007, in accordance with Repair 10, dated April 15, 2006, of Chapter
53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-
300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215;
or Boeing 767-400 SRM, Document D634T225; as applicable; is
acceptable for compliance with the requirements of paragraph (g) of
this AD for that area only.
New Requirements of This AD
Inspections
(k) At the later of the times specified in paragraphs (k)(1) and
(k)(2) of this AD, except as specified in paragraph (l) of this AD:
Do the detailed and HFEC inspections for cracking as specified in
Parts 5 and 6 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-53A0131, Revision 1, dated March 12, 2009; and
do all applicable corrective actions by accomplishing all the
actions specified in the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-53A0131, Revision 1, dated March 12, 2009;
except as provided by paragraph (h) of this AD. Do all applicable
corrective actions before further flight. Repeat the inspections
thereafter at intervals not to exceed 6,000 flight cycles.
Accomplishing the corrective action for the inspections specified in
Part 5 or 6 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-53A0131, Revision 1, dated March 12, 2009, as
applicable, terminates the repetitive inspections for that area
only.
(1) 15,000 total flight cycles or 6,000 flight cycles after the
inspection required by paragraph (g) of this AD, whichever occurs
first.
(2) 30 days after the effective date of this AD.
Exceptions to the Service Bulletin
(l) Where Boeing Alert Service Bulletin 767-53A0131, Revision 1,
dated March 12, 2009, specifies a compliance time ``after the date
on the original issue of the service bulletin'' or ``after the date
on Revision 01 of the service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
Optional Terminating Action for the Repetitive Inspections Required by
Paragraph (k) of This AD
(m) If no cracking is found during the most recent detailed and
HFEC inspections for a specified area as required by paragraph (k)
of this AD: Modification of a specified area in accordance with a
method approved by the Manager, Seattle ACO, FAA, terminates the
repetitive inspections required by paragraph (k) of this AD for that
area only.
Note 1: Guidance on modifying a vertical inner chord can be
found in the service information identified in Table 1 of this AD.
Table 1--Service Information
----------------------------------------------------------------------------------------------------------------
Steps-- Dated-- Of--
----------------------------------------------------------------------------------------------------------------
4.A through 4.C and 4.G through 4.Q of August 15, 2008........................ Chapter 53[dash]80-08 of the
Repair 11. Boeing 767-200 SRM,
Document D634T201.
4.A through 4.C and 4.G through 4.Q of August 15, 2008........................ Chapter 53[dash]80-08 of the
Repair 11. Boeing 767-300 SRM,
Document D634T210.
4.A through 4.C and 4.G through 4.Q of August 15, 2008........................ Chapter 53[dash]80-08 of the
Repair 11. Boeing 767-300F SRM,
Document D634T215.
4.A through 4.C and 4.G through 4.Q of August 15, 2008........................ Chapter 53[dash]80-08 of the
Repair 11. Boeing 767-400 SRM,
Document D634T225.
----------------------------------------------------------------------------------------------------------------
[[Page 6157]]
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN: Berhane Alazar, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6577; fax (425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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 previously in accordance with AD 2006-24-04
are approved as AMOCs for the corresponding provisions of this AD.
Issued in Renton, Washington, on January 28, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-2685 Filed 2-5-10; 8:45 am]
BILLING CODE 4910-13-P
