Airworthiness Directives; Boeing Model 727-200 Series Airplanes Equipped With a No. 3 Cargo Door, 35385-35387 [06-5498]

Download as PDF Federal Register / Vol. 71, No. 118 / Tuesday, June 20, 2006 / Rules and Regulations Issued in Renton, Washington, on June 9, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5500 Filed 6–19–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24073; Directorate Identifier 2002–NM–272–AD; Amendment 39–14653; AD 2006–13–01] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727–200 Series Airplanes Equipped With a No. 3 Cargo Door Examining the Docket Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727–200 series airplanes. That AD currently requires initial and repetitive inspections for cracks in the forward frame of the No. 3 cargo door cutout; and corrective actions, if necessary. The existing AD also provides for an optional structural modification, which terminates the repetitive inspections. This new AD reduces the compliance time for the initial inspections and adds an optional method of inspection for both the initial and repetitive inspections. This AD also adds initial and repetitive inspections of an additional area, and repair if necessary. Additionally, this AD clarifies that the previously optional structural modification is now required by other rulemaking. This AD results from additional reports of cracking in the forward frame of the No. 3 cargo door cutout. We are issuing this AD to detect and correct cracking of the forward frame and fuselage skin of the No. 3 cargo door cutout, which could result in failure of the frame and skin, and consequent rapid decompression of the airplane. DATES: This AD becomes effective July 25, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 25, 2006. wwhite on PROD1PC61 with RULES SUMMARY: VerDate Aug<31>2005 15:58 Jun 19, 2006 Jkt 208001 You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: ADDRESSES: You may examine the airworthiness directive (AD) docket on the Internet at http://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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 86–17–05 R1, amendment 39–5714 (52 FR 32534, August 28, 1987). The existing AD applies to certain Boeing Model 727– 200 series airplanes. That NPRM was published in the Federal Register on March 7, 2006 (71 FR 11345). That NPRM proposed to continue to require initial and repetitive inspections for cracks in the forward frame of the No. 3 cargo door cutout; and corrective actions, if necessary. That NPRM proposed to reduce the compliance time for the initial inspections and add an optional method of inspection for both the initial and repetitive inspections. That NPRM also proposed to add initial and repetitive inspections of an additional area, and repair if necessary. Additionally, that NPRM clarified that the previously optional structural modification is now required by other rulemaking. Comments We provided the public the opportunity to participate in the PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 35385 development of this AD. We have considered the comments that have been received on the NPRM. Request for Clarification of Certain Language Boeing requests that certain language be added to the Actions Since Existing AD was Issued section of the NPRM to clarify that the forward frame is the subject of the findings and that the skin and doubler in the area are also involved as an area of concern. We agree that adding the suggested language would clarify the location of the subject unsafe condition (i.e., the forward frame of the No. 3 cargo door cutout, along with the surrounding skin and doubler). However, because that section of the NPRM is not restated in the final rule, we find that no change to the AD is necessary in this regard. Request To Correct AD Number in Restatement of Requirements Heading Boeing points out that there is a typographical error in the AD number identified in the ‘‘REQUIREMENTS OF AD 86–17–05 R1 WITH REDUCED THRESHOLD AND NEW OPTIONAL INSPECTION METHOD:’’ heading in the regulatory text of the NPRM, and requests that the error, ‘‘AD 86–17–05 RL,’’ be corrected to read ‘‘AD 86–17– 05 R1.’’ We agree. We have verified that an error did occur in the AD number in that heading during printing of the NPRM. That AD number is correct in this final rule. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 269 airplanes of the affected design in the worldwide fleet. The new requirements of this AD add no additional economic burden. The current costs for U.S. operators to comply with this AD are repeated for the convenience of affected operators, as follows: E:\FR\FM\20JNR1.SGM 20JNR1 35386 Federal Register / Vol. 71, No. 118 / Tuesday, June 20, 2006 / Rules and Regulations ESTIMATED COSTS Action Work hours Inspections (required by AD 86–17–05 RI), per inspection cycle. Average labor rate per hour 6 $65 Cost per airplane None ........ $390, per inspection cycle .... Authority for This Rulemaking Adoption of the Amendment 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. I wwhite on PROD1PC61 with RULES Regulatory Findings We have determined that 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); 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 AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–5714 (52 FR 32534, August 28, 1987) and by adding the following new airworthiness directive (AD): I 2006–13–01 Boeing: Amendment 39–14653. Docket No. FAA–2006–24073; Directorate Identifier 2002–NM–272–AD. Effective Date (a) This AD becomes effective July 25, 2006. Affected ADs (b) This AD supersedes AD 86–17–05 R1. Applicability (c) This AD applies to Boeing Model 727– 200 series airplanes, certificated in any category, equipped with a No. 3 cargo door, as identified in Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986. Unsafe Condition (d) This AD results from additional reports of cracking in the forward frame of the No. 3 cargo door cutout. We are issuing this AD to detect and correct cracking of the forward frame and fuselage skin of the No. 3 cargo door cutout, which could result in failure of the frame and consequent rapid decompression 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. List of Subjects in 14 CFR Part 39 Requirements of AD 86–17–05 R1 With Reduced Threshold and New Optional Inspection Method Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Inspections (f) At the earlier of the times specified in paragraphs (f)(1) and (f)(2) of this AD: Do a VerDate Aug<31>2005 15:58 Jun 19, 2006 Jkt 208001 PO 00000 Number of U.S.-registered airplanes Parts cost Frm 00014 Fmt 4700 Sfmt 4700 166 Fleet cost $64,740, per inspection cycle. penetrant or detailed inspection of the forward frame of the No. 3 cargo door cutout for cracking, in accordance with paragraph C. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986. After the effective date of this AD, the penetrant or detailed inspection must be done in accordance with paragraph 3.B.3. of the Accomplishment Instructions of Boeing Service Bulletin 727–53A0169, Revision 6, dated September 28, 2002. If any cracking is found, repair in accordance with paragraph (h) or (l) of this AD, as applicable. Repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. (1) Within the next 300 flight cycles after September 3, 1987 (the effective date of AD 86–17–05 R1), or prior to accumulating 29,000 total flight cycles, whichever occurs later, unless accomplished within the last 1,900 flight cycles. (2) Prior to accumulating 18,000 total flight cycles, or within 2,200 flight cycles after the effective date of this AD, whichever occurs later. (g) At the earlier of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a detailed inspection of the forward frame of the No. 3 cargo door cutout for cracking, in accordance with paragraphs D. and E. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986. After the effective date of this AD, the detailed inspection must be done in accordance with paragraphs 3.B.4. and 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 727– 53A0169, Revision 6, dated September 28, 2002. If any cracking is found, repair in accordance with paragraph (h) or (l) of this AD, as applicable. Repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. (1) Within the next 300 flight cycles after September 3, 1987, or prior to accumulating 35,000 total flight cycles, whichever occurs later, unless accomplished within the last 1,900 flight cycles. (2) Prior to accumulating 18,000 total flight cycles, or within 2,200 flight cycles after the effective date of this AD, whichever occurs later. Repair (h) Before further flight, repair any crack in the forward frame of the No. 3 cargo door cutout found before the effective date of this AD during any inspection required by paragraph (f) or (g) of this AD, in accordance with paragraph G. of the Accomplishment E:\FR\FM\20JNR1.SGM 20JNR1 35387 Federal Register / Vol. 71, No. 118 / Tuesday, June 20, 2006 / Rules and Regulations Instructions in Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986. Repeat the inspections specified in paragraphs (f) and (g) of this AD at intervals not to exceed 2,200 flight cycles, for all areas of the forward frame not covered by the repair, in accordance with the Accomplishment Instructions of paragraphs C., D., and E. of Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986. New Requirements of This AD Inspection of Repairs of the Frame Done Before the Effective Date of the AD (i) For any repair to the forward frame of the No. 3 cargo door cutout done, as required by paragraph (h) of this AD, before the effective date of this AD: Within 18,000 flight cycles following the repair, or 2,200 flight cycles after the effective date of this AD, whichever occurs later, do a detailed inspection of the repair for cracking in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727– 53A0169, Revision 6, dated September 28, 2002. Thereafter, repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ New Inspections of Skin Surrounding the Frame (j) Prior to the accumulation of 18,000 total flight cycles, or within 2,200 flight cycles after the effective date of this AD, whichever occurs later: Do a penetrant or detailed inspection for cracking of the fuselage skin of the No. 3 cargo door cutout between stringers S–24 and S–27, in accordance with paragraph 3.B.3. of the Accomplishment Instructions of Boeing Service Bulletin 727– 53A0169, Revision 6, dated September 28, 2002. Repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. wwhite on PROD1PC61 with RULES Repair of Cracked Skin (k) If any crack is found in the fuselage skin during any inspection required by paragraph (j) of this AD: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Repair of Cracked Frames and Post—Repair Inspections (l) If, after the effective date of this AD, any crack is found in the forward frame of the No. 3 cargo door cutout during any inspection required by paragraph (f), (g), or (i) of this AD: Before further flight, do the actions specified in paragraph (l)(1), (l)(2), or (l)(3) of this AD, as applicable. Inspect the repair VerDate Aug<31>2005 15:58 Jun 19, 2006 Jkt 208001 within 18,000 flight cycles following the repair, in accordance with paragraphs 3.B.4. and 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 727– 53A0169, Revision 6, dated September 28, 2002. Thereafter, repeat the inspections at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. (1) If cracks have not severed the inner flange, do an interim repair using a method approved in accordance with the procedures specified in paragraph (p) of this AD. (2) Repair the crack in accordance with paragraph 3.B.7.b. of the Accomplishment Instructions of Boeing Service Bulletin 727– 53A0169, Revision 6, dated September 28, 2002. (3) Replace the cracked segment of the frame with a new or serviceable component and install the frame reinforcement preventative modification, in accordance with paragraph 3.B.7.c. of the Accomplishment Instructions of Boeing Service Bulletin 727–53A0169, Revision 6, dated September 28, 2002. This action terminates the requirements of this AD. Repairs Done According to Previous Issues of the Service Bulletin (m) Inspections and repairs done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986; Boeing Service Bulletin 727–53A0169, Revision 3, dated June 11, 1987; Revision 4, dated January 21, 1988; and Revision 5, dated November 2, 1989, are acceptable for compliance with the corresponding requirements of paragraphs (h), (k), and (l) of this AD, as applicable. Terminating Modification Required by AD 90–06–09 (n) At the same time as the applicable inspections provided in paragraphs (f), (g), (i), and (j) of this AD are accomplished, doing the frame reinforcement preventative modification required by paragraph A. of AD 90–06–09 or the frame reinforcement preventative modification specified in Figure 2 of Boeing Service Bulletins 727–53A0169, Revision 5, dated November 2, 1989; and Revision 6, dated September 28, 2002; terminates the requirements of this AD. Paragraph A. of AD 90–06–09 references Boeing Document D6–54860, Revision C, dated December 11, 1989, ‘‘Aging Airplane Structural Modification Program—Model 727’’ as the appropriate source of service information for accomplishing the frame reinforcement preventative modification (along with numerous other structural modifications required by paragraph A. of AD 90–06–09). Information Submission (o) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (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 an Authorized Representative for the Boeing Commercial Airplanes 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. (4) An AMOC approved previously in accordance with AD 86–17–05 R1, is approved as an AMOC with the corresponding requirements and provisions of this AD. Material Incorporated by Reference (q) You must use Boeing Alert Service Bulletin 727–53A0169, Revision 2, dated May 23, 1986; or Boeing Service Bulletin 727–53A0169, Revision 6, dated September 28, 2002; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Boeing Alert Service Bulletin 727–53A0169, Revision 2, contains the following effective pages: Page number Revision level shown on page Date shown on page 2 1 May 23, 1986. March 28, 1986. 1, 3–16 ..... 2 ............... Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, 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 June 9, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5498 Filed 6–19–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\20JNR1.SGM 20JNR1

Agencies

[Federal Register Volume 71, Number 118 (Tuesday, June 20, 2006)]
[Rules and Regulations]
[Pages 35385-35387]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5498]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24073; Directorate Identifier 2002-NM-272-AD; 
Amendment 39-14653; AD 2006-13-01]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727-200 Series Airplanes 
Equipped With a No. 3 Cargo Door

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 727-200 series airplanes. 
That AD currently requires initial and repetitive inspections for 
cracks in the forward frame of the No. 3 cargo door cutout; and 
corrective actions, if necessary. The existing AD also provides for an 
optional structural modification, which terminates the repetitive 
inspections. This new AD reduces the compliance time for the initial 
inspections and adds an optional method of inspection for both the 
initial and repetitive inspections. This AD also adds initial and 
repetitive inspections of an additional area, and repair if necessary. 
Additionally, this AD clarifies that the previously optional structural 
modification is now required by other rulemaking. This AD results from 
additional reports of cracking in the forward frame of the No. 3 cargo 
door cutout. We are issuing this AD to detect and correct cracking of 
the forward frame and fuselage skin of the No. 3 cargo door cutout, 
which could result in failure of the frame and skin, and consequent 
rapid decompression of the airplane.

DATES: This AD becomes effective July 25, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 25, 2006.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 86-17-05 R1, amendment 
39-5714 (52 FR 32534, August 28, 1987). The existing AD applies to 
certain Boeing Model 727-200 series airplanes. That NPRM was published 
in the Federal Register on March 7, 2006 (71 FR 11345). That NPRM 
proposed to continue to require initial and repetitive inspections for 
cracks in the forward frame of the No. 3 cargo door cutout; and 
corrective actions, if necessary. That NPRM proposed to reduce the 
compliance time for the initial inspections and add an optional method 
of inspection for both the initial and repetitive inspections. That 
NPRM also proposed to add initial and repetitive inspections of an 
additional area, and repair if necessary. Additionally, that NPRM 
clarified that the previously optional structural modification is now 
required by other rulemaking.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request for Clarification of Certain Language

    Boeing requests that certain language be added to the Actions Since 
Existing AD was Issued section of the NPRM to clarify that the forward 
frame is the subject of the findings and that the skin and doubler in 
the area are also involved as an area of concern.
    We agree that adding the suggested language would clarify the 
location of the subject unsafe condition (i.e., the forward frame of 
the No. 3 cargo door cutout, along with the surrounding skin and 
doubler). However, because that section of the NPRM is not restated in 
the final rule, we find that no change to the AD is necessary in this 
regard.

Request To Correct AD Number in Restatement of Requirements Heading

    Boeing points out that there is a typographical error in the AD 
number identified in the ``REQUIREMENTS OF AD 86-17-05 R1 WITH REDUCED 
THRESHOLD AND NEW OPTIONAL INSPECTION METHOD:'' heading in the 
regulatory text of the NPRM, and requests that the error, ``AD 86-17-05 
RL,'' be corrected to read ``AD 86-17-05 R1.''
    We agree. We have verified that an error did occur in the AD number 
in that heading during printing of the NPRM. That AD number is correct 
in this final rule.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We have determined that this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 269 airplanes of the affected design in the 
worldwide fleet. The new requirements of this AD add no additional 
economic burden. The current costs for U.S. operators to comply with 
this AD are repeated for the convenience of affected operators, as 
follows:

[[Page 35386]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Number of
                                Work     Average                       Cost per        U.S.-
            Action              hours   labor rate    Parts cost       airplane      registered     Fleet cost
                                         per hour                                    airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD         6          $65  None.........  $390, per                166  $64,740, per
 86-17-05 RI), per inspection                                       inspection                    inspection
 cycle.                                                             cycle.                        cycle.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this 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); 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 AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-5714 (52 FR 32534, August 28, 1987) and by adding 
the following new airworthiness directive (AD):

2006-13-01 Boeing: Amendment 39-14653. Docket No. FAA-2006-24073; 
Directorate Identifier 2002-NM-272-AD.

Effective Date

    (a) This AD becomes effective July 25, 2006.

Affected ADs

    (b) This AD supersedes AD 86-17-05 R1.

Applicability

    (c) This AD applies to Boeing Model 727-200 series airplanes, 
certificated in any category, equipped with a No. 3 cargo door, as 
identified in Boeing Alert Service Bulletin 727-53A0169, Revision 2, 
dated May 23, 1986.

Unsafe Condition

    (d) This AD results from additional reports of cracking in the 
forward frame of the No. 3 cargo door cutout. We are issuing this AD 
to detect and correct cracking of the forward frame and fuselage 
skin of the No. 3 cargo door cutout, which could result in failure 
of the frame and consequent rapid decompression 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.

Requirements of AD 86-17-05 R1 With Reduced Threshold and New Optional 
Inspection Method

Inspections

    (f) At the earlier of the times specified in paragraphs (f)(1) 
and (f)(2) of this AD: Do a penetrant or detailed inspection of the 
forward frame of the No. 3 cargo door cutout for cracking, in 
accordance with paragraph C. of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 
1986. After the effective date of this AD, the penetrant or detailed 
inspection must be done in accordance with paragraph 3.B.3. of the 
Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, 
Revision 6, dated September 28, 2002. If any cracking is found, 
repair in accordance with paragraph (h) or (l) of this AD, as 
applicable. Repeat the inspection at intervals not to exceed 2,200 
flight cycles, until the preventative modification specified in 
paragraph (n) of this AD is done.
    (1) Within the next 300 flight cycles after September 3, 1987 
(the effective date of AD 86-17-05 R1), or prior to accumulating 
29,000 total flight cycles, whichever occurs later, unless 
accomplished within the last 1,900 flight cycles.
    (2) Prior to accumulating 18,000 total flight cycles, or within 
2,200 flight cycles after the effective date of this AD, whichever 
occurs later.
    (g) At the earlier of the times specified in paragraphs (g)(1) 
and (g)(2) of this AD: Do a detailed inspection of the forward frame 
of the No. 3 cargo door cutout for cracking, in accordance with 
paragraphs D. and E. of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986. 
After the effective date of this AD, the detailed inspection must be 
done in accordance with paragraphs 3.B.4. and 3.B.5. of the 
Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, 
Revision 6, dated September 28, 2002. If any cracking is found, 
repair in accordance with paragraph (h) or (l) of this AD, as 
applicable. Repeat the inspection at intervals not to exceed 2,200 
flight cycles, until the preventative modification specified in 
paragraph (n) of this AD is done.
    (1) Within the next 300 flight cycles after September 3, 1987, 
or prior to accumulating 35,000 total flight cycles, whichever 
occurs later, unless accomplished within the last 1,900 flight 
cycles.
    (2) Prior to accumulating 18,000 total flight cycles, or within 
2,200 flight cycles after the effective date of this AD, whichever 
occurs later.

Repair

    (h) Before further flight, repair any crack in the forward frame 
of the No. 3 cargo door cutout found before the effective date of 
this AD during any inspection required by paragraph (f) or (g) of 
this AD, in accordance with paragraph G. of the Accomplishment

[[Page 35387]]

Instructions in Boeing Alert Service Bulletin 727-53A0169, Revision 
2, dated May 23, 1986. Repeat the inspections specified in 
paragraphs (f) and (g) of this AD at intervals not to exceed 2,200 
flight cycles, for all areas of the forward frame not covered by the 
repair, in accordance with the Accomplishment Instructions of 
paragraphs C., D., and E. of Boeing Alert Service Bulletin 727-
53A0169, Revision 2, dated May 23, 1986.

New Requirements of This AD

Inspection of Repairs of the Frame Done Before the Effective Date 
of the AD

    (i) For any repair to the forward frame of the No. 3 cargo door 
cutout done, as required by paragraph (h) of this AD, before the 
effective date of this AD: Within 18,000 flight cycles following the 
repair, or 2,200 flight cycles after the effective date of this AD, 
whichever occurs later, do a detailed inspection of the repair for 
cracking in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 
2002. Thereafter, repeat the inspection at intervals not to exceed 
2,200 flight cycles, until the preventative modification specified 
in paragraph (n) of this AD is done.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

New Inspections of Skin Surrounding the Frame

    (j) Prior to the accumulation of 18,000 total flight cycles, or 
within 2,200 flight cycles after the effective date of this AD, 
whichever occurs later: Do a penetrant or detailed inspection for 
cracking of the fuselage skin of the No. 3 cargo door cutout between 
stringers S-24 and S-27, in accordance with paragraph 3.B.3. of the 
Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, 
Revision 6, dated September 28, 2002. Repeat the inspection at 
intervals not to exceed 2,200 flight cycles, until the preventative 
modification specified in paragraph (n) of this AD is done.

Repair of Cracked Skin

    (k) If any crack is found in the fuselage skin during any 
inspection required by paragraph (j) of this AD: Before further 
flight, repair the crack using a method approved in accordance with 
the procedures specified in paragraph (p) of this AD.

Repair of Cracked Frames and Post--Repair Inspections

    (l) If, after the effective date of this AD, any crack is found 
in the forward frame of the No. 3 cargo door cutout during any 
inspection required by paragraph (f), (g), or (i) of this AD: Before 
further flight, do the actions specified in paragraph (l)(1), 
(l)(2), or (l)(3) of this AD, as applicable. Inspect the repair 
within 18,000 flight cycles following the repair, in accordance with 
paragraphs 3.B.4. and 3.B.5. of the Accomplishment Instructions of 
Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 
2002. Thereafter, repeat the inspections at intervals not to exceed 
2,200 flight cycles, until the preventative modification specified 
in paragraph (n) of this AD is done.
    (1) If cracks have not severed the inner flange, do an interim 
repair using a method approved in accordance with the procedures 
specified in paragraph (p) of this AD.
    (2) Repair the crack in accordance with paragraph 3.B.7.b. of 
the Accomplishment Instructions of Boeing Service Bulletin 727-
53A0169, Revision 6, dated September 28, 2002.
    (3) Replace the cracked segment of the frame with a new or 
serviceable component and install the frame reinforcement 
preventative modification, in accordance with paragraph 3.B.7.c. of 
the Accomplishment Instructions of Boeing Service Bulletin 727-
53A0169, Revision 6, dated September 28, 2002. This action 
terminates the requirements of this AD.

Repairs Done According to Previous Issues of the Service Bulletin

    (m) Inspections and repairs done before the effective date of 
this AD in accordance with Boeing Alert Service Bulletin 727-
53A0169, Revision 2, dated May 23, 1986; Boeing Service Bulletin 
727-53A0169, Revision 3, dated June 11, 1987; Revision 4, dated 
January 21, 1988; and Revision 5, dated November 2, 1989, are 
acceptable for compliance with the corresponding requirements of 
paragraphs (h), (k), and (l) of this AD, as applicable.

Terminating Modification Required by AD 90-06-09

    (n) At the same time as the applicable inspections provided in 
paragraphs (f), (g), (i), and (j) of this AD are accomplished, doing 
the frame reinforcement preventative modification required by 
paragraph A. of AD 90-06-09 or the frame reinforcement preventative 
modification specified in Figure 2 of Boeing Service Bulletins 727-
53A0169, Revision 5, dated November 2, 1989; and Revision 6, dated 
September 28, 2002; terminates the requirements of this AD. 
Paragraph A. of AD 90-06-09 references Boeing Document D6-54860, 
Revision C, dated December 11, 1989, ``Aging Airplane Structural 
Modification Program--Model 727'' as the appropriate source of 
service information for accomplishing the frame reinforcement 
preventative modification (along with numerous other structural 
modifications required by paragraph A. of AD 90-06-09).

Information Submission

    (o) Although the service bulletins referenced in this AD specify 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (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 an 
Authorized Representative for the Boeing Commercial Airplanes 
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.
    (4) An AMOC approved previously in accordance with AD 86-17-05 
R1, is approved as an AMOC with the corresponding requirements and 
provisions of this AD.

Material Incorporated by Reference

    (q) You must use Boeing Alert Service Bulletin 727-53A0169, 
Revision 2, dated May 23, 1986; or Boeing Service Bulletin 727-
53A0169, Revision 6, dated September 28, 2002; as applicable, to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise. The Director of the Federal Register approved 
the incorporation by reference of these documents in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51. Boeing Alert Service Bulletin 
727-53A0169, Revision 2, contains the following effective pages:

------------------------------------------------------------------------
                                    Revision
          Page  number            level shown      Date shown on page
                                    on page
------------------------------------------------------------------------
1, 3-16.........................            2  May 23, 1986.
2...............................            1  March 28, 1986.
------------------------------------------------------------------------

Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, 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 June 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5498 Filed 6-19-06; 8:45 am]
BILLING CODE 4910-13-P