Document ID: FAA-2010-0646-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Model 727; et al.
Posted Date: 2010-07-01T04:00Z

[Federal Register: July 1, 2010 (Volume 75, Number 126)]
[Proposed Rules]               
[Page 38066-38068]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01jy10-28]                         

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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 me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at 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
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                   Average
              Action                 Work hours   labor rate          Parts             Cost per product       Number of U.S.-           Fleet cost
                                                   per hour                                                  registered airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\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: 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.

    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