Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes, 24335-24338 [05-9187]
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Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Proposed Rules
Establish the Number of Landings
(g) At the applicable time specified in
paragraph (f) of this AD: If a component does
not have a S/N and the CSN or TSN were not
tracked, use the formula in the applicable
Messier-Dowty service bulletin in Table 2 of
this AD to establish the number of landings
(TSN or CSN), and record the newly
calculated TSN or CSN in the aircraft log
books.
Revise the Airworthiness Limitations
Section (ALS)
(h) Within 30 days after the effective date
of this AD, revise the ALS of the applicable
Instructions for Continued Airworthiness to
reflect the new life limits of the landing gear
24335
parts by inserting copies of the Canadair
temporary revisions (TR) in Table 3 of this
AD into the ALS of the applicable Canadair
Time-Limits/Maintenance Check Manual.
When the contents of the TRs are included
in the general revisions of the ALS, these TRs
may be removed provided the relevant
information in the ALS is identical to that in
the TRs.
TABLE 3.—CANADAIR TEMPORARY REVISIONS
Temporary revision
Applicable Canadair time-limits/maintenance check manual
5–116, dated April 11, 2002 ....
5–190, dated April 11, 2002 ....
PSP 605 ..................................
PSP 601–5 ..............................
5–10–10
5–10–10
5–191, dated April 11, 2002 ....
PSP 601–5 ..............................
5–10–11
5–192, dated April 11, 2002 ....
PSP 601–5 ..............................
5–10–12
5–2–6, dated April 11, 2002 ....
5–204, dated April 11, 2002 ....
CL–604 ...................................
PSP 601A–5 ...........................
5–10–10
5–10–10
5–205, dated April 11, 2002 ....
PSP 601A–5 ...........................
5–10–11
5–206, dated April 11, 2002 ....
PSP 601A–5 ...........................
5–10–12
Parts Installation
(i) As of the effective date of this AD, no
person may install on any airplane a landing
gear part, unless it has had the applicable
part number (P/N) or serial number (S/N)
added in accordance with paragraph (f) of
this AD; and had the number of landings
established in accordance with paragraph (g)
of this AD.
(j) Although the service bulletins identified
in paragraph (f) of this AD request that
operators submit incorporation notices to
Bombardier after each new P/N or S/N and
landings assigned to these parts is added, this
AD does not include that action.
Actions Done in Accordance With Previous
Issues of Service Bulletins
(k) Actions done before the effective date
of this AD in accordance with Bombardier
Service Bulletin 601–0546, dated May 31,
2002; and Bombardier Service Bulletin 600–
0710, dated May 31, 2002; are acceptable for
compliance with the corresponding action
specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(l) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Related Information
(m) Canadian airworthiness directives CF–
2003–18R1, dated January 17, 2005; CF–
2003–20, dated July 24, 2003; and CF–2003–
21R1, dated January 21, 2005; also address
the subject of this AD.
15:24 May 06, 2005
Model
CL600–1A11 (CL–600) series airplanes
CL–600–2A12 (CL–601) and CL–600–2B16
CL–601–3R) series airplanes
CL–600–2A12 (CL–601) and CL–600–2B16
CL–601–3R) series airplanes
CL–600–2A12 (CL–601) and CL–600–2B16
CL–601–3R) series airplanes
CL–600–2B16 (CL–604) series airplanes
CL–600–2A12 (CL–601) and CL–600–2B16
CL–601–3R) series airplanes
CL–600–2A12 (CL–601) and CL–600–2B16
CL–601–3R) series airplanes
CL–600–2A12 (CL–601) and CL–600–2B16
CL–601–3R) series airplanes
Issued in Renton, Washington, on April 29,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–9186 Filed 5–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
No Reporting Required
VerDate jul<14>2003
Manual
section
Jkt 205001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21138; Directorate
Identifier 2004–NM–131–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, and –200C Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–100, –200,
and –200C series airplanes. This
proposed AD would require a one-time
detailed inspection for cracking of the
lugs of the inboard attach fittings of the
wing leading edge slat tracks at slat
numbers 2 and 5; prior or concurrent
actions for certain airplanes; repetitive
high-frequency eddy current (HFEC)
inspections for cracking of the lug
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
(CL–601–3A and
(CL–601–3A and
(CL–601–3A and
(CL–601–3A and
(CL–601–3A and
(CL–601–3A and
surfaces of those inboard attach fittings
if necessary; and replacement of the
attach fittings with new, improved
fittings. This proposed AD is prompted
by reports of damage to the lugs of
certain inboard attach fittings of the
leading edge slat tracks. We are
proposing this AD to prevent a lifted
slat, which, if the airplane performs any
non-normal maneuver during takeoff or
landing at very high angles of attack,
could lead to the loss of the slat and
reduced control of the airplane.
DATES: We must receive comments on
this proposed AD by June 23, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to http:
//dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, 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, P.O. Box 3707,
Seattle, Washington 98124–2207.
E:\FR\FM\09MYP1.SGM
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24336
Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Proposed Rules
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21138; the directorate identifier for this
docket is 2004–NM–131–AD.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21138; Directorate Identifier
2004–NM–131–AD’’ in the subject line
of your comments. We specifically
invite comments on the overall
regulatory, economic, environmental,
and energy aspects of the proposed AD.
We will consider all comments
submitted by the closing date and may
amend the proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
We have received reports of damage
to the lugs of the inboard attach fittings
of the wing leading edge slat tracks at
slat numbers 2 and 5 on several Boeing
Model 737–100, –200, and –200C series
airplanes. Two reports addressed
damage that occurred during takeoff and
four reports addressed damage that
occurred during flight. The other
damaged fittings were found during
routine maintenance inspections. In
most of the reports, the lugs of the
fittings had fractured or cracked. Both
lugs of one fitting had fractured and
were completely separated at the slat-totrack attach bolt. The auxiliary track
was also lifted and there was damage to
the upper skin of the leading edge cavity
on each side. Boeing analysis has
determined this fitting damage was due
to cyclic fatigue. This condition, if not
corrected, could result in a lifted slat,
which, if the airplane performs any nonnormal maneuver during takeoff or
landing at very high angles of attack,
could lead to loss of the slat and
reduced control of the airplane.
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 737–57–
1273, Revision 2, dated October 30,
2003. The service bulletin describes
procedures for a one-time detailed
visual inspection for cracking of the lugs
of the inboard attach fittings at slat
tracks 2 and 5 of the wing leading edge,
repetitive high-frequency eddy current
(HFEC) inspections for cracking of the
lug surfaces of those inboard attach
fittings, and replacement of the
aluminum inboard attach fittings with
new, improved steel inboard attach
fittings. Replacement of any aluminum
inboard attach fitting with a new,
improved steel inboard attach fitting
eliminates the need for the one-time
detailed inspection and the repetitive
HFEC inspections for that fitting.
Accomplishing the actions specified in
the service bulletin is intended to
adequately address the unsafe
condition.
Service Bulletin 737–57–1273,
Revision 2, specifies prior
accomplishment of portions of Boeing
Service Bulletin 737–57–1080, Revision
3, dated September 24, 1992 (applicable
to Group 2 airplanes only as listed in
Service Bulletin 737–57–1273). Among
other things, Service Bulletin 737–57–
1080, Revision 3, Figure 3, describes
procedures for inspecting the slat tab
support clip on slats 2 and 5 for
interference with the slat track inboard
attach fittings and trimming the subject
slat tab support clips to eliminate any
such interference.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. Therefore, we are
proposing this AD, which would require
a one-time detailed inspection for
cracking of the lugs of the inboard
attach fittings at slat tracks 2 and 5 of
the wing leading edge, related
investigative actions, trimming the slat
tab support clip on slats 2 and 5 to
eliminate any interference with the slat
track inboard attach fittings if necessary,
and replacing the attach fittings with
new, improved fittings. Replacement of
any aluminum inboard attach fitting
with a new, improved steel inboard
attach fitting terminates the one-time
detailed inspection and the repetitive
HFEC inspections for that fitting. The
proposed AD would require you to use
the service information described
previously to perform these actions,
except as discussed under ‘‘Clarification
of Inspection Terminology.’’
Clarification of Inspection Terminology
In this proposed AD, the ‘‘detailed
visual inspection’’ specified in the
Boeing service bulletin is referred to as
a ‘‘detailed inspection.’’ We have
included the definition for a detailed
inspection in the proposed AD.
Costs of Compliance
This proposed AD would affect about
909 airplanes worldwide. The following
table provides the estimated costs for
U.S. operators to comply with this
proposed AD.
ESTIMATED COSTS
Action
Work
hours
Detailed inspection .......
VerDate jul<14>2003
15:24 May 06, 2005
Average labor
rate per hour
1
Jkt 205001
$65
PO 00000
Parts cost
Cost per airplane
None ...........................
Number of
U.S.-registered
airplanes
$65 ..............................
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E:\FR\FM\09MYP1.SGM
522
09MYP1
Fleet cost
$33,930
Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Proposed Rules
24337
ESTIMATED COSTS—Continued
Action
Work
hours
Average labor
rate per hour
Parts cost
Cost per airplane
230, per inspection
cycle..
1,804 ...........................
HFEC Inspection ..........
4
65
None ...........................
Replace fitting ..............
2
65
$1,674 .........................
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
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 adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–21138;
Directorate Identifier 2004–NM–131–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by June 23, 2005.
Affected ADs
(b) None.
We have determined that this
proposed AD would not have federalism
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. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
Applicability
(c) This AD applies to Boeing Model 737–
100, –200, and –200C series airplanes; line
numbers 1 through 1585 inclusive;
certificated in any category.
List of Subjects in 14 CFR Part 39
Inspections
(g) Prior to the accumulation of 7,000 total
flight cycles or within 12 months after the
effective date of this AD, whichever occurs
Air transportation, Aircraft, Aviation
safety, Safety.
VerDate jul<14>2003
15:24 May 06, 2005
Jkt 205001
Unsafe Condition
(d) This AD was prompted by reports of
damage to the lugs of certain inboard attach
fittings of the leading edge slat tracks. We are
issuing this AD to prevent a lifted slat,
which, if the airplane performs any nonnormal maneuver during takeoff or landing at
very high angles of attack, could lead to the
loss of the slat and reduced control of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–57–1273, Revision 2,
dated October 30, 2003; unless otherwise
specified in this AD.
PO 00000
Number of
U.S.-registered
airplanes
Frm 00012
Fmt 4702
Sfmt 4702
522
522
Fleet cost
120,060, per inspection cycle.
941,688
later, perform a one-time detailed inspection
for cracking and damage of the inboard attach
fittings at slats 2 and 5 of the wing leading
edge in accordance with the
Accomplishment Instructions of the service
bulletin.
Note 1: For the purposes of this AD, a
detailed inspection is ‘‘An intensive visual
examination of a specific structural area,
system, installation, or assembly to detect
damage, failure, or irregularity. Available
lighting is normally supplemented with a
direct source of good lighting at intensity
deemed appropriate by the inspector.
Inspection aids such as mirror, magnifying
lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be
required.’’
(1) If any crack or damage is found, replace
the cracked inboard attach fitting in
accordance with paragraph (h) of this AD.
(2) If no crack or damage is found, within
4,500 flight cycles or 18 months after the
detailed inspection required by paragraph (g)
of this AD, whichever occurs first, perform a
high-frequency eddy current (HFEC)
inspection for cracking of the lugs of the
inboard attach fittings in accordance with the
Accomplishment Instructions of the service
bulletin. If no crack is found, repeat the
HFEC inspection at intervals not to exceed
4,500 flight cycles.
Replacement of Fittings
(h) Replace the aluminum inboard attach
fittings with new, improved steel fittings at
the applicable compliance time in paragraph
(h)(1) or (h)(2) of this AD in accordance with
the Accomplishment Instructions of the
service bulletin. Replacement of any
aluminum fitting with a new, improved steel
fitting terminates the one-time detailed
inspection and the repetitive HFEC
inspections required by paragraph (g) of this
AD for that fitting.
(1) If any crack or damage is found during
any inspection required by paragraphs (g) or
(i) of this AD, before further flight.
(2) If no crack or damage is found during
any inspection required by paragraph (g) or
(i) of this AD, within 30,000 flight cycles or
within 120 months after the effective date of
this AD, whichever occurs first.
Concurrent Service Bulletin
(i) For airplanes listed in Group 2 of Boeing
Special Attention Service Bulletin 737–57–
1273, Revision 2: Prior to or during the onetime detailed inspection for cracking or
damage required by paragraph (g) of this AD
or during replacement of the fitting required
by paragraph (h) of this AD, whichever
occurs first, perform a detailed inspection on
slats 2 and 5 for interference of the slat tab
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09MYP1
24338
Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Proposed Rules
support clips with the slat track attach
fittings and trim the support clips to
eliminate any interference with the attach
fittings as applicable; in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–57–1080, Revision 3,
Figure 3, dated September 24, 1992; and
replace any cracked or damaged aluminum
attach fitting with a new, improved steel
fitting in accordance with paragraph (h) of
this AD.
Actions Accomplished Per Previous Issue of
Service Bulletin
(j) Actions accomplished before the
effective date of this AD in accordance with
Boeing Service Bulletin 737–57–1080, dated
September 10, 1973; Boeing Service Bulletin
737–57–1080, Revision 1, dated February 25,
1983; and Boeing Service Bulletin 737–57–
1080, Revision 2, dated August 24, 1989; are
considered acceptable for compliance with
the corresponding actions specified in
paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Delegation Option Authorization
Organization who 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.
Issued in Renton, Washington, on April 29,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–9187 Filed 5–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21140; Directorate
Identifier 2004–NM–274–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–9–14, DC–9–15,
and DC–9–15F Airplanes; and
McDonnell Douglas Model DC–9–20,
DC–9–30, DC–9–40, and DC–9–50
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate jul<14>2003
15:24 May 06, 2005
Jkt 205001
Notice of proposed rulemaking
(NPRM).
ACTION:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
transport category airplanes listed
above. This proposed AD would require
repetitive inspections for cracks of the
main landing gear (MLG) shock strut
cylinder, and related investigative and
corrective actions if necessary. This
proposed AD is prompted by two
reports of a collapsed MLG and a report
of cracks in two MLG cylinders. We are
proposing this AD to detect and correct
fatigue cracks in the shock strut cylinder
of the MLG, which could result in a
collapsed MLG during takeoff or
landing, and possible reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by June 23, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, 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, Long Beach
Division, 3855 Lakewood Boulevard,
Long Beach, California 90846,
Attention: Data and Service
Management, Dept. C1–L5A (D800–
0024).
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Room PL–401, on the plaza level
of the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21140; the directorate identifier for this
docket is 2004–NM–274–AD.
FOR FURTHER INFORMATION CONTACT:
Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5324; fax (562) 627–5210.
SUMMARY:
PO 00000
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Fmt 4702
Sfmt 4702
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21140; Directorate Identifier
2004–NM–274–AD’’ in the subject line
of your comments. We specifically
invite comments on the overall
regulatory, economic, environmental,
and energy aspects of the proposed AD.
We will consider all comments
submitted by the closing date and may
amend the proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that
website, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
We have received a report of two
incidents of a collapsed main landing
gear (MLG) on one McDonnell Douglas
Model DC–9–32 airplane and one Model
DC–9–31 airplane. These incidents
happened when the MLG cylinder
cracked and failed. The cracks and
failures were caused by fatigue stresses
from inclusions in high-stress areas,
which caused sub-surface fatigue cracks
to propagate to the surface of the MLG
cylinder. After the two failures, the
airplane operator started an inspection
program and found cracks in two
additional cylinders before the cracks
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]]>Agencies
[Federal Register Volume 70, Number 88 (Monday, May 9, 2005)]
[Proposed Rules]
[Pages 24335-24338]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-9187]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21138; Directorate Identifier 2004-NM-131-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, and -200C
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 737-100, -200, and -200C series airplanes.
This proposed AD would require a one-time detailed inspection for
cracking of the lugs of the inboard attach fittings of the wing leading
edge slat tracks at slat numbers 2 and 5; prior or concurrent actions
for certain airplanes; repetitive high-frequency eddy current (HFEC)
inspections for cracking of the lug surfaces of those inboard attach
fittings if necessary; and replacement of the attach fittings with new,
improved fittings. This proposed AD is prompted by reports of damage to
the lugs of certain inboard attach fittings of the leading edge slat
tracks. We are proposing this AD to prevent a lifted slat, which, if
the airplane performs any non-normal maneuver during takeoff or landing
at very high angles of attack, could lead to the loss of the slat and
reduced control of the airplane.
DATES: We must receive comments on this proposed AD by June 23, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http: //dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, 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, P.O. Box 3707, Seattle, Washington 98124-
2207.
[[Page 24336]]
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-21138; the directorate identifier for this docket is
2004-NM-131-AD.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6440; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-21138;
Directorate Identifier 2004-NM-131-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
We have received reports of damage to the lugs of the inboard
attach fittings of the wing leading edge slat tracks at slat numbers 2
and 5 on several Boeing Model 737-100, -200, and -200C series
airplanes. Two reports addressed damage that occurred during takeoff
and four reports addressed damage that occurred during flight. The
other damaged fittings were found during routine maintenance
inspections. In most of the reports, the lugs of the fittings had
fractured or cracked. Both lugs of one fitting had fractured and were
completely separated at the slat-to-track attach bolt. The auxiliary
track was also lifted and there was damage to the upper skin of the
leading edge cavity on each side. Boeing analysis has determined this
fitting damage was due to cyclic fatigue. This condition, if not
corrected, could result in a lifted slat, which, if the airplane
performs any non-normal maneuver during takeoff or landing at very high
angles of attack, could lead to loss of the slat and reduced control of
the airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 737-57-
1273, Revision 2, dated October 30, 2003. The service bulletin
describes procedures for a one-time detailed visual inspection for
cracking of the lugs of the inboard attach fittings at slat tracks 2
and 5 of the wing leading edge, repetitive high-frequency eddy current
(HFEC) inspections for cracking of the lug surfaces of those inboard
attach fittings, and replacement of the aluminum inboard attach
fittings with new, improved steel inboard attach fittings. Replacement
of any aluminum inboard attach fitting with a new, improved steel
inboard attach fitting eliminates the need for the one-time detailed
inspection and the repetitive HFEC inspections for that fitting.
Accomplishing the actions specified in the service bulletin is intended
to adequately address the unsafe condition.
Service Bulletin 737-57-1273, Revision 2, specifies prior
accomplishment of portions of Boeing Service Bulletin 737-57-1080,
Revision 3, dated September 24, 1992 (applicable to Group 2 airplanes
only as listed in Service Bulletin 737-57-1273). Among other things,
Service Bulletin 737-57-1080, Revision 3, Figure 3, describes
procedures for inspecting the slat tab support clip on slats 2 and 5
for interference with the slat track inboard attach fittings and
trimming the subject slat tab support clips to eliminate any such
interference.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require a one-time detailed inspection for cracking of the lugs
of the inboard attach fittings at slat tracks 2 and 5 of the wing
leading edge, related investigative actions, trimming the slat tab
support clip on slats 2 and 5 to eliminate any interference with the
slat track inboard attach fittings if necessary, and replacing the
attach fittings with new, improved fittings. Replacement of any
aluminum inboard attach fitting with a new, improved steel inboard
attach fitting terminates the one-time detailed inspection and the
repetitive HFEC inspections for that fitting. The proposed AD would
require you to use the service information described previously to
perform these actions, except as discussed under ``Clarification of
Inspection Terminology.''
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in the Boeing service bulletin is referred to as a ``detailed
inspection.'' We have included the definition for a detailed inspection
in the proposed AD.
Costs of Compliance
This proposed AD would affect about 909 airplanes worldwide. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work Average labor Parts cost Cost per airplane registered Fleet cost
hours rate per hour airplanes
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Detailed inspection................. 1 $65 None................... $65.................... 522 $33,930
[[Page 24337]]
HFEC Inspection..................... 4 65 None................... 230, per inspection 522 120,060, per inspection
cycle.. cycle.
Replace fitting..................... 2 65 $1,674................. 1,804.................. 522 941,688
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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
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. 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, 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 adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2005-21138; Directorate Identifier 2004-NM-
131-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by June 23, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-100, -200, and -200C
series airplanes; line numbers 1 through 1585 inclusive;
certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of damage to the lugs of
certain inboard attach fittings of the leading edge slat tracks. We
are issuing this AD to prevent a lifted slat, which, if the airplane
performs any non-normal maneuver during takeoff or landing at very
high angles of attack, could lead to the loss of the slat and
reduced control of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-57-1273, Revision 2, dated October 30, 2003; unless
otherwise specified in this AD.
Inspections
(g) Prior to the accumulation of 7,000 total flight cycles or
within 12 months after the effective date of this AD, whichever
occurs later, perform a one-time detailed inspection for cracking
and damage of the inboard attach fittings at slats 2 and 5 of the
wing leading edge in accordance with the Accomplishment Instructions
of the service bulletin.
Note 1: For the purposes of this AD, a detailed inspection is
``An intensive visual examination of a specific structural area,
system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.''
(1) If any crack or damage is found, replace the cracked inboard
attach fitting in accordance with paragraph (h) of this AD.
(2) If no crack or damage is found, within 4,500 flight cycles
or 18 months after the detailed inspection required by paragraph (g)
of this AD, whichever occurs first, perform a high-frequency eddy
current (HFEC) inspection for cracking of the lugs of the inboard
attach fittings in accordance with the Accomplishment Instructions
of the service bulletin. If no crack is found, repeat the HFEC
inspection at intervals not to exceed 4,500 flight cycles.
Replacement of Fittings
(h) Replace the aluminum inboard attach fittings with new,
improved steel fittings at the applicable compliance time in
paragraph (h)(1) or (h)(2) of this AD in accordance with the
Accomplishment Instructions of the service bulletin. Replacement of
any aluminum fitting with a new, improved steel fitting terminates
the one-time detailed inspection and the repetitive HFEC inspections
required by paragraph (g) of this AD for that fitting.
(1) If any crack or damage is found during any inspection
required by paragraphs (g) or (i) of this AD, before further flight.
(2) If no crack or damage is found during any inspection
required by paragraph (g) or (i) of this AD, within 30,000 flight
cycles or within 120 months after the effective date of this AD,
whichever occurs first.
Concurrent Service Bulletin
(i) For airplanes listed in Group 2 of Boeing Special Attention
Service Bulletin 737-57-1273, Revision 2: Prior to or during the
one-time detailed inspection for cracking or damage required by
paragraph (g) of this AD or during replacement of the fitting
required by paragraph (h) of this AD, whichever occurs first,
perform a detailed inspection on slats 2 and 5 for interference of
the slat tab
[[Page 24338]]
support clips with the slat track attach fittings and trim the
support clips to eliminate any interference with the attach fittings
as applicable; in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 737-57-1080, Revision 3, Figure 3, dated
September 24, 1992; and replace any cracked or damaged aluminum
attach fitting with a new, improved steel fitting in accordance with
paragraph (h) of this AD.
Actions Accomplished Per Previous Issue of Service Bulletin
(j) Actions accomplished before the effective date of this AD in
accordance with Boeing Service Bulletin 737-57-1080, dated September
10, 1973; Boeing Service Bulletin 737-57-1080, Revision 1, dated
February 25, 1983; and Boeing Service Bulletin 737-57-1080, Revision
2, dated August 24, 1989; are considered acceptable for compliance
with the corresponding actions specified in paragraph (i) of this
AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Delegation Option
Authorization Organization who 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.
Issued in Renton, Washington, on April 29, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-9187 Filed 5-6-05; 8:45 am]
BILLING CODE 4910-13-P
