[Federal Register Volume 75, Number 126 (Thursday, July 1, 2010)]
[Proposed Rules]
[Pages 38066-38068]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-15989]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0646; Directorate Identifier 2009-NM-223-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 727, 727C,
727-100, 727-100C, 727-200, and 727-200F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series
airplanes. This proposed AD would require repetitive detailed
inspections of the aft pressure bulkhead web for cracking, and repair
if necessary. For certain airplanes, this proposed AD also would
provide for an optional preventative modification of the aft pressure
bulkhead web, which would terminate certain repetitive detailed
inspections. This proposed AD results from reports of cracks in the aft
pressure bulkhead web. We are proposing this AD to detect and correct
cracking in the aft pressure bulkhead web, which could adversely affect
the structural integrity of the airplane, resulting in difficulty
maintaining cabin pressurization or rapid decompression of the
airplane.
DATES: We must receive comments on this proposed AD by August 16, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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 [email protected];
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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, Aerospace Engineer,
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-2010-0646;
Directorate Identifier 2009-NM-223-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 http://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
We have received 13 reports of cracks in the aft pressure bulkhead
web ranging from 0.75 inch to 11.8 inches in length at the buttock line
61, between water line (WL) 220 and WL 228. The cracks originated at
the hydraulic line support brackets, which were installed in production
after airplane line number 1136, or in accordance with Boeing Service
Bulletin 727-29-0057. The cracks were found in airplanes that had
accumulated between 14,939 total flight hours and 39,369 total flight
hours, and between 10,685 total flight cycles and 29,357 total flight
cycles. The cracking is attributed to fatigue of the aft pressure
bulkhead web due to vibrations from the number 1 engine hydraulic pump
line, in addition to normal pressurization cycles. Material analysis
revealed multiple crack initiation sites and no evidence of corrosion.
This condition, if not corrected, could result in difficulty
maintaining cabin pressurization or rapid decompression of the
airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 727-53-
0232, dated September 23, 2009. This service bulletin describes
procedures for initial and repetitive detailed inspections of the aft
pressure bulkhead web for any cracking around the hydraulic line
support bracket, and repair of any crack found. For certain airplanes,
this service bulletin describes procedures for installing an optional
preventative modification if no cracking is found during the detailed
inspections. The preventative modification includes doing high
frequency eddy current
[[Page 38067]]
(HFEC) inspections of the open fastener holes and installing a
modification doubler on the aft side of the bulkhead web, which would
eliminate the need for certain repetitive inspections. If any cracking
is found during the detailed or HFEC inspection, this service bulletin
specifies contacting Boeing for repair instructions and installing the
repair.
The compliance times for the initial inspection range between 3,500
flight cycles from the date on the service bulletin and 7,000 flight
cycles since the previous inspection. The compliance time for repairing
any cracking is before further flight. The interval for repeating the
detailed inspection ranges between 1,000 flight cycles and 12,000
flight cycles, depending on airplane configuration, the time since the
last inspection, and the type of the last inspection.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD and the Service Information.''
Differences Between the Proposed AD and the Service Information
Boeing Special Attention Service Bulletin 727-53-0232, dated
September 23, 2009, specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Boeing Special Attention Service Bulletin 727-53-0232, dated
September 23, 2009, provides damage tolerance inspections in Table 3 of
paragraph 1.E. of that service bulletin. Note 1 of this proposed AD
relates to these damage tolerance inspections, which are not required
for compliance with this proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect 243 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Table--Estimated Costs
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Average
Action Work hours labor rate Parts Cost per product Number of U.S.- Fleet cost
per hour registered airplanes
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Detailed inspection, per 1 $85 None................. $85, per inspection 243.................. $20,655, per
inspection cycle. cycle. inspection cycle.
Preventative modification......... 4 $85 Negligible\1\........ $340................. Up to 243............ Up to $82,620.
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\1\ The cost of material for the modification would depend on the size and location of the repair; the materials necessary for the modification are
standard shop materials that would be provided out of the operator's stock.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0646; Directorate Identifier
2009-NM-223-AD.
Comments Due Date
(a) We must receive comments by August 16, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all The Boeing Company Model 727, 727C,
727-100, 727-
[[Page 38068]]
100C, 727-200, and 727-200F series airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of cracks in the aft pressure
bulkhead web. The Federal Aviation Administration is issuing this AD
to prevent cracking in the aft pressure bulkhead web, which could
adversely affect the structural integrity of the airplane, resulting
in difficulty maintaining cabin pressurization or rapid
decompression of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Repetitive Inspections and Corrective Actions
(g) At the applicable initial compliance time specified in
Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 727-53-0232, dated September 23, 2009
(``the service bulletin''); except as provided by paragraph (j) of
this AD: Perform a detailed inspection for cracking in the area
around the hydraulic line support bracket on the aft side of the aft
pressure bulkhead web between water line (WL) 217 to WL 230, and
buttock line (BL) 48 left to BL 66 left. Do the inspection in
accordance with the Accomplishment Instructions of the service
bulletin.
(1) For Group 1, Configuration 1 airplanes, and Group 2
airplanes, as identified in the service bulletin: If no cracking is
found during the inspection required by paragraph (g) of this AD, do
the actions specified in paragraph (g)(1)(i) or (g)(1)(ii) of this
AD in accordance with the Accomplishment Instructions of the service
bulletin.
(i) Accomplish the preventative modification specified in PART 3
of the service bulletin before further flight.
(ii) Repeat the detailed inspection at the applicable interval
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of
the service bulletin. Accomplishing the preventative modification
specified in paragraph (g)(1)(i) of this AD terminates the
repetitive inspections required by this paragraph.
(2) For Group 1, Configuration 2 airplanes, as identified in the
service bulletin: If no cracking is found during the inspection
required by paragraph (g) of this AD, repeat the detailed inspection
at the applicable interval specified in Tables 1 and 2 of paragraph
1.E., ``Compliance,'' of the service bulletin.
Note 1: The damage tolerance inspections specified in Table 3 of
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 727-53-0232, dated September 23, 2009, may be used in
support of compliance with section 121.1109(c)(2) or 129.109(c)(2)
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR
129.109(c)(2)).
(h) If any crack is found during any inspection required by
paragraph (g) of this AD, before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 727-53-0232, dated September 23, 2009;
except as provided by paragraph (i) of this AD.
(i) If any cracking is found during any inspection required by
this AD, and Boeing Special Attention Service Bulletin 727-53-0232,
dated September 23, 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 (k) of this AD.
(j) Where Boeing Special Attention Service Bulletin 727-53-0232,
dated September 23, 2009, specifies a compliance time after the date
on that service bulletin, this AD requires compliance within the
specified compliance time after the effective date 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
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Berhane Alazar, Aerospace Engineer, 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. Information may be e-mailed to: [email protected].
(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.
Issued in Renton, Washington, on June 25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-15989 Filed 6-30-10; 8:45 am]
BILLING CODE 4910-13-P