[Federal Register Volume 76, Number 6 (Monday, January 10, 2011)]
[Rules and Regulations]
[Pages 1339-1342]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-188]


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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; 
Amendment 39-16558; AD 2011-01-05]
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: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD requires repetitive detailed inspections 
of the aft pressure bulkhead web for cracking, and repair if necessary. 
For certain airplanes, this AD also provides for an optional 
preventative modification of the aft pressure bulkhead web, which would 
terminate certain repetitive detailed inspections. This AD was prompted 
by reports of cracks in the aft pressure bulkhead web. We are issuing 
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: This AD is effective February 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 14, 
2011.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; 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

[[Page 1340]]

Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The address for the Docket Office (phone: 800-647-5527) is Document 
Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
the specified products. That NPRM was published in the Federal Register 
on July 1, 2010 (75 FR 38066). That NPRM proposed to require repetitive 
detailed inspections of the aft pressure bulkhead web for cracking, and 
repair if necessary. For certain airplanes, that NPRM also proposed an 
optional preventative modification of the aft pressure bulkhead web, 
which would terminate certain repetitive detailed inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following paragraphs present the comments received on the 
proposal and the FAA's response to each comment.

Request To Rephrase Unsafe Condition Statement in the AD

    Boeing requested that we change the second sentence of paragraph 
(e) of the AD to state that the FAA ``is issuing this AD to detect and 
repair cracking, or to modify structure to prevent cracking, in the aft 
pressure bulkhead web * * *'' The commenter stated that the original 
paragraph specified that the AD is being issued ``to prevent 
cracking,'' whereas the AD provides modification instructions to 
prevent cracking, as well as instructions to repair cracking, and the 
requested language is more correct.
    We partially agree with the commenter's request. We agree to change 
the AD to say ``detect and correct cracking'' because the AD provides 
those instructions, and we have changed paragraph (e) accordingly. We 
disagree with including ``modify structure to prevent cracking'' 
because the AD does not mandate the preventive modification. The 
modification to prevent cracking is available as an option in the AD 
and in Boeing Special Attention Service Bulletin 727-53-0232, dated 
September 23, 2009, the service information referenced in the NPRM; we 
have made no further change to the AD in this regard.

Request To Remove Description From Paragraph (g) of the AD

    Boeing requested that we remove ``* * * in the area around the 
hydraulic line support bracket on the left side * * *'' from paragraph 
(g) of the AD. The commenter stated that airplanes in Group 1, 
Configuration 2, do not have that hydraulic bracket installed, and 
therefore cannot be inspected ``around the bracket.'' Boeing stated 
further that the service bulletin specifies an inspection in the entire 
bay of the web, and the requested change would cover all the subject 
airplanes and prevent confusion.
    We agree with the commenter's request, for the reasons given, and 
we have changed paragraph (g) of the AD accordingly.

Request To Correct Table Reference in Paragraph (g)(2) of the AD

    Boeing requested that in paragraph (g)(2) of the NPRM we refer only 
to Table 2 of paragraph 1.E., ``Compliance,'' in Boeing Special 
Attention Service Bulletin 727-53-0232, dated September 23, 2009, for 
the applicable compliance time. The commenter stated that paragraph 
(g)(2) of the AD covers only airplanes of Group 1, Configuration 2, 
which are addressed only in Table 2 of paragraph 1.E. of that service 
bulletin.
    We agree with the commenter's request, for the reasons given, and 
we have changed paragraph (g)(2) of the AD accordingly. We have also 
changed paragraph (g)(1)(ii) of this AD to only refer to Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009.

Clarification of Terminating Action

    We have clarified that for Group 1, Configuration 1 airplanes, and 
Group 2 airplanes, as identified in Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009, doing the repair 
specified in paragraph (h) of the AD terminates the repetitive 
inspections required by paragraph (g)(1)(ii) of the AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 243 airplanes of U.S. registry. 
The following table provides the estimated costs for U.S. operators to 
comply with this AD.

                                                                                     Table--Estimated Costs
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                                                    Average
               Action                 Work hours   labor rate             Parts                   Cost per product        Number of U.S.- registered                  Fleet cost
                                                    per hour                                                                      airplanes
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Detailed inspection, per inspection            1          $85  None.......................  $85, per inspection cycle..  243........................  $20,655, per inspection cycle.
 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

[[Page 1341]]

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2011-01-05 The Boeing Company: Amendment 39-16558; Docket No. FAA-
2010-0646; Directorate Identifier 2009-NM-223-AD.

Effective Date

    (a) This AD is effective February 14, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all The Boeing Company Model 727, 727C, 
727-100, 727-100C, 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 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.

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; 
except as provided by paragraph (j) of this AD: Perform a detailed 
inspection for cracking 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 Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009.
    (1) For Group 1, Configuration 1 airplanes, and Group 2 
airplanes, as identified in Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009: 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 Boeing 
Special Attention Service Bulletin 727-53-0232, dated September 23, 
2009.
    (i) Accomplish the preventative modification specified in Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 727-53-0232, dated September 23, 2009, before 
further flight.
    (ii) Repeat the detailed inspection at the applicable interval 
specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 727-53-0232, dated September 23, 
2009. 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 
Boeing Special Attention Service Bulletin 727-53-0232, dated 
September 23, 2009: 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 Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 727-53-
0232, dated September 23, 2009.

    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. For Group 1, 
Configuration 1 airplanes, and Group 2 airplanes, as identified in 
Boeing Special Attention Service Bulletin 727-53-0232, dated 
September 23, 2009: Accomplishing this repair terminates the 
repetitive inspections required by paragraph (g)(1)(ii) 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.

[[Page 1342]]

Related Information

    (l) For more information about this AD, 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.

Material Incorporated by Reference

    (m) You must use Boeing Special Attention Service Bulletin 727-
53-0232, dated September 23, 2009, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
[email protected]; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-188 Filed 1-7-11; 8:45 am]
BILLING CODE 4910-13-P