Airworthiness Directives; Boeing Model 707 Airplanes, and Model 720 and 720B Series Airplanes, 46331-46334 [E9-20838]

Download as PDF Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–18–13 Rolls-Royce plc: Amendment 39–16009.; Docket No. FAA–2009–0771; Directorate Identifier 2009–NE–14–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 14, 2009. Affected ADs (b) None. jlentini on DSKJ8SOYB1PROD with RULES Applicability (c) This AD applies to Rolls-Royce plc (RR) model RB211 Trent 970–84, 970B–84, 972– 84, 972B–84, 977–84, 977B–84, and 980–84 turbofan engines that do not incorporate RR modification Service Bulletin (SB) RB.211– 72–G025. These engines are installed on, but not limited to, Airbus A380 airplanes. Reason (d) Evidence from development testing and flight test Trent 900 engines has identified cracking on some HP Turbine Nozzle Guide Vane (NGV) Convex Surfaces. Analysis of test data and review of the manufacturing process has revealed compounding effects that may contribute to a shortfall in component life and an increased likelihood of premature cracking in this region. Excessive cracking on the Convex Surface may lead to the release of NGV material or the blockage of Turbine gas flow. This results in a risk of fracture to the HP Turbine Blade. We are issuing this AD to prevent the release of a high-pressure (HP) turbine blade, which could result in an engine power loss or in-flight shut down of one or more VerDate Nov<24>2008 16:13 Sep 08, 2009 Jkt 217001 engines, resulting in an inability to continue safe flight. Actions and Compliance First Inspection (e) Before accumulating 400 total cycles, inspect the HPT NGV Convex Surfaces, in accordance with the accomplishment instructions in section 3.A of Rolls-Royce RB211–Trent 900 Alert Non Modification Service Bulletin (NMSB) RB.211–72–AF995 Revision 2, dated February 9, 2009. Reinspection (f) If no damage is identified at first inspection: (1) Repeat the inspection at intervals less than 250 Cycles apart. (2) If repeat inspections reveal no damage at 1000 cycles revert to normal inspection maintenance as detailed in the Rolls-Royce RB211–Trent 900 Maintenance Planning Document (MPD), and sign off this AD as complied with; no further inspections are required by this AD. (g) If any damage is identified, refer to the Table 1 and Table 2 in section 3.B. of RollsRoyce RB211–Trent 900 Alert NMSB RB.211–72–AF995 Revision 2, dated February 9, 2009, for reinspection intervals and rejection criteria. FAA AD Differences (h) None. Other FAA AD Provisions (i) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (j) Refer to MCAI EASA Airworthiness Directive 2009–0051, dated March 5, 2009. (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park; Burlington, MA 01803; e-mail: ian.dargin@faa.gov; telephone (781) 238–7178; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (l) You must use RR Alert Non Mandatory Service Bulletin RB.211–72–AF995 Revision 2, dated February 9, 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 Rolls-Royce plc, P.O. Box 31, DERBY, DE24 8BJ, UK; telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 46331 Issued in Burlington, Massachusetts, on August 20, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–20830 Filed 9–8–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0476; Directorate Identifier 2008–NM–188–AD; Amendment 39–16006; AD 2009–18–10] RIN 2120–AA64 Airworthiness Directives; Boeing Model 707 Airplanes, and Model 720 and 720B Series Airplanes 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 707 airplanes, and Model 720 and 720B series airplanes. The existing AD currently requires repetitive detailed inspections to detect cracks and corrosion on any existing repairs and at certain body stations (STA) of the visible surfaces of the wing to body terminal fittings including the web, flanges, and ribs; and applicable related investigative and corrective actions. This new AD retains the requirements of the existing AD and requires repetitive ultrasonic inspections to detect any stress corrosion cracks within the outboard flange of the left and right body terminal fittings at STA 820, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD also adds two airplanes to the applicability. This AD results from reports of cracks found in the wing to body terminal fittings during routine inspections. We are issuing this AD to detect and correct cracks and corrosion in the body terminal fittings above and below the floor, which could cause loss of support for the wing and could adversely affect the structural integrity of the airplane. DATES: This AD becomes effective October 14, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 14, 2009. E:\FR\FM\09SER1.SGM 09SER1 46332 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 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 me.boecom@boeing.com; Internet https://www.myboeingfleet.com. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the 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: optional terminating action for the repetitive inspections. That NPRM also proposed to add two airplanes to the applicability. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2008–17–10, amendment 39–15648 (73 FR 50703, August 28, 2008). The existing AD applies to certain Boeing Model 707 airplanes, and Model 720 and 720B series airplanes. That NPRM was published in the Federal Register on May 26, 2009 (74 FR 24715). That NPRM proposed to continue to require detailed inspections and applicable related investigative and corrective actions. That NPRM also proposed to require repetitive ultrasonic inspections to detect any stress corrosion cracks within the outboard flange of the left and right body terminal fittings at station (STA) 820, and related investigative and corrective actions if necessary. That NPRM also proposed an We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been received on the NPRM. The commenter concurs with the content of the NPRM. Comments Conclusion We have carefully reviewed the available data, including the comment that has been received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 128 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Average labor rate per hour Action Work hours Inspections (required by AD 2008–17–10). Inspections (new required action). 20 ................................... $80 20 to 30, depending on group. Number of U.S.registered irplanes Cost per airplane 80 $1,600 per inspection cycle. $1,600 to $2,400 per inspection cycle. 11 ..................... Up to 13 ........... Fleet cost $17,600 per inspection cycle. Up to $31,200 per inspection cycle. jlentini on DSKJ8SOYB1PROD with RULES Authority for This Rulemaking Regulatory Findings List of Subjects in 14 CFR Part 39 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. 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Nov<24>2008 16:13 Sep 08, 2009 Jkt 217001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–15648 (73 FR 50703, August 28, 2008) and by adding the following new airworthiness directive (AD): ■ E:\FR\FM\09SER1.SGM 09SER1 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 2009–18–10 Boeing: Amendment 39–16006. Docket No. FAA–2009–0476; Directorate Identifier 2008–NM–188–AD. Effective Date (a) This AD becomes effective October 14, 2009. Affected ADs (b) This AD supersedes AD 2008–17–10, amendment 39–15648. Applicability (c) This AD applies to Boeing Model 707– 100 long body, –200, –100B long body, and –100B short body series airplanes; Model 707–300, –300B, –300C, and –400 series airplanes; and Model 720 and 720B series airplanes; certificated in any category; as identified in Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Unsafe Condition (e) This AD results from new findings of cracks found in the wing to body terminal fittings during routine inspections. We are issuing this AD to detect and correct cracks and corrosion in the body terminal fittings above and below the floor, which could cause loss of support for the wing and could adversely affect the structural integrity 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. jlentini on DSKJ8SOYB1PROD with RULES Restatement of Requirements of AD 2008– 17–10 With Updated Service Information Inspections and Corrective Actions (g) For airplanes identified in Boeing 707 Special Attention Service Bulletin 3524, dated July 18, 2007: Within 24 months after October 2, 2008 (the effective date of AD 2008–17–10), do detailed inspections and applicable related investigative and corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing 707 Special Attention Service Bulletin 3524, dated July 18, 2007; or Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008; except as provided by paragraph (h) of this AD. After the effective date of this AD, use only Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008. Repeat the detailed inspections thereafter at intervals not to exceed 24 months. Do all applicable related investigative and corrective actions before further flight. (h) If any crack or corrosion is found during any inspection required by paragraph (g) of this AD, and Boeing 707 Special Attention Service Bulletin 3524, dated July 18, 2007, or Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair the terminal fittings using a method VerDate Nov<24>2008 16:13 Sep 08, 2009 Jkt 217001 approved in accordance with the procedures specified in paragraph (o) of this AD. No Information Submission (i) Although Boeing 707 Special Attention Service Bulletin 3524, dated July 18, 2007; and Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008; specify to submit information to the manufacturer, this AD does not include that requirement. New Requirements of This AD Inspections (j) For Group 1 and Group 2 airplanes identified in Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, on which a modification or repair was done in accordance with Boeing 707/720 Service Bulletin 2912, Revision 1, dated March 13, 1970: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do an ultrasonic inspection to detect any stress corrosion cracks within the outboard flange of the left and right body terminal fittings at body station (STA) 820, and all applicable related investigative and corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, except as provided by paragraph (m) of this AD. Repeat the ultrasonic inspection thereafter at intervals not to exceed 24 months or 2,000 flight cycles, whichever occurs first. Do all applicable related investigative and corrective actions before further flight. (1) Within 24 months or 2,000 flight cycles after the effective date of this AD, whichever occurs first. (2) Within 24 months or 2,000 flight cycles after doing the repair or modification, whichever occurs first. (k) For Group 3 and Group 4 airplanes identified in Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008: Within 2,000 flight cycles or 24 months after the effective date of this AD, whichever occurs first, do an ultrasonic inspection to detect any stress corrosion cracks within the outboard flange of the left and right body terminal fittings at STA 820, and all applicable corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, except as provided by paragraph (m) of this AD. Repeat the ultrasonic inspection thereafter at intervals not to exceed 24 months or 2,000 flight cycles, whichever occurs first. Do all applicable corrective actions before further flight. (l) For Group 4 airplanes identified in Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008: Within 24 months after the effective date of this AD, do detailed inspections for corrosion and cracking of the body terminal fittings at STA 820, and all applicable related investigative and corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, except as PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 46333 provided by paragraph (m) of this AD. Repeat the detailed inspections thereafter at intervals not to exceed 24 months. Do all applicable related investigative and corrective actions before further flight. Exception to Certain Procedures (m) If any crack or corrosion is found during any inspection required by paragraph (j), (k), or (l) of this AD, and Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair the terminal fittings using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Note 1: Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, refers to Boeing 707/720 Service Bulletin 2912, Revision 1, dated March 13, 1970, as an additional source of guidance for doing certain inspections and repairs. Optional Terminating Action (n) Replacing a body terminal fitting with a fitting made from 7075–T73 material, using a method approved in accordance with the procedures specified in paragraph (o) of this AD, terminates the repetitive inspections required by this AD for that fitting only. Alternative Methods of Compliance (AMOCs) (o)(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; or, e-mail information 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 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. Material Incorporated by Reference (p) You must use Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 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 E:\FR\FM\09SER1.SGM 09SER1 46334 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 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 me.boecom@boeing.com; 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 or 425–227–1152. (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 NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 18, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–20838 Filed 9–8–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0515; Directorate Identifier 2008–NM–071–AD; Amendment 39–16007; AD 2009–18–11] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: jlentini on DSKJ8SOYB1PROD with RULES SUMMARY: Following a red illuminated ‘‘DOOR NOT LOCKED’’ status light indication on the door lock indication panel after lift off, the cabin crew operated the door lock handle. This resulted in inadvertent opening of the downward opening passenger door in flight. * * * After inspection, it was found that the false red light might be the result of an incorrect VerDate Nov<24>2008 16:13 Sep 08, 2009 Jkt 217001 clearance between lever Part Number (P/N) A26997–003 and the Up-Limit Switch. If the Up-Limit Switch has an incorrect clearance, the combination with cabin differential pressure build-up after lift-off might result in a false steady illuminating red ‘‘DOOR NOT LOCKED’’ indication on the Door Indication Panel. * * * * * * * * The unsafe condition is inadvertent opening of the door lock handle in flight, which could result in rapid decompression of the airplane or ejection of a passenger or crewmember through the door. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 14, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 14, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on June 9, 2009 (74 FR 27260). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Following a red illuminated ‘‘DOOR NOT LOCKED’’ status light indication on the door lock indication panel after lift off, the cabin crew operated the door lock handle. This resulted in inadvertent opening of the downward opening passenger door in flight. It appeared that the cabin crew was unaware of the content of Fokker 70/100 Service Letter (SL) 272. This SL informs not to operate the door lock handle after the aircraft has started to move or before it has come to a complete standstill. After inspection, it was found that the false red light might be the result of an incorrect clearance between lever Part Number (P/N) A26997–003 and the Up-Limit Switch. If the Up-Limit Switch has an incorrect clearance, the combination with cabin differential pressure build-up after lift-off might result in a false steady illuminating red ‘‘DOOR NOT PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 LOCKED’’ indication on the Door Indication Panel. The original Fokker Service Bulletin SBF100–52–044 and the associated Aircraft Maintenance Manual (AMM) task mentioned a clearance of 1,3 mm ± 0,3 mm. Later, based on a trial, an improved clearance of 0,3 mm ± 0,2 mm was introduced. Both documents have been revised for that reason. Later production serial number aircraft with downward opening passenger doors had the correct clearance introduced before delivery, but no action was taken to inspect and adjust the clearance on previously delivered or modified (per SBF100–52–044) serial numbers. Since an unsafe condition has been identified that is likely to exist or develop on other aircraft of the same type design, this [EASA] Airworthiness Directive (AD) requires two actions: —The installation of a warning placard near the status lights of the door lock indication panel, instructing the cabin crew not to operate the door handle during flight and to inform the flight crew of the ‘‘DOOR NOT LOCKED’’ indication; and —A one-time inspection of the clearance between lever P/N A26997–003 and the Up-Limit Switch. If this clearance deviates from the limits given in AMM task 52–71– 01–400–814–A, which is 0,3 mm ± 0,2 mm (0.0118 inch ± 0.0079 inch), corrective actions are required. The unsafe condition is inadvertent opening of the door lock handle in flight, which could result in rapid decompression of the airplane or ejection of a passenger or crewmember through the door. The corrective action for improper clearance is adjusting the clearance between the lever and the uplimit switch. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. E:\FR\FM\09SER1.SGM 09SER1

Agencies

[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46331-46334]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20838]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0476; Directorate Identifier 2008-NM-188-AD; 
Amendment 39-16006; AD 2009-18-10]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 707 Airplanes, and Model 
720 and 720B Series Airplanes

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 707 airplanes, and Model 
720 and 720B series airplanes. The existing AD currently requires 
repetitive detailed inspections to detect cracks and corrosion on any 
existing repairs and at certain body stations (STA) of the visible 
surfaces of the wing to body terminal fittings including the web, 
flanges, and ribs; and applicable related investigative and corrective 
actions. This new AD retains the requirements of the existing AD and 
requires repetitive ultrasonic inspections to detect any stress 
corrosion cracks within the outboard flange of the left and right body 
terminal fittings at STA 820, and related investigative and corrective 
actions if necessary. This AD also provides an optional terminating 
action for the repetitive inspections. This AD also adds two airplanes 
to the applicability. This AD results from reports of cracks found in 
the wing to body terminal fittings during routine inspections. We are 
issuing this AD to detect and correct cracks and corrosion in the body 
terminal fittings above and below the floor, which could cause loss of 
support for the wing and could adversely affect the structural 
integrity of the airplane.

DATES: This AD becomes effective October 14, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 14, 
2009.

[[Page 46332]]


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 me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the 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

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2008-17-10, amendment 
39-15648 (73 FR 50703, August 28, 2008). The existing AD applies to 
certain Boeing Model 707 airplanes, and Model 720 and 720B series 
airplanes. That NPRM was published in the Federal Register on May 26, 
2009 (74 FR 24715). That NPRM proposed to continue to require detailed 
inspections and applicable related investigative and corrective 
actions. That NPRM also proposed to require repetitive ultrasonic 
inspections to detect any stress corrosion cracks within the outboard 
flange of the left and right body terminal fittings at station (STA) 
820, and related investigative and corrective actions if necessary. 
That NPRM also proposed an optional terminating action for the 
repetitive inspections. That NPRM also proposed to add two airplanes to 
the applicability.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
received on the NPRM. The commenter concurs with the content of the 
NPRM.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined that air safety and the 
public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 128 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                             Average  labor                           Number of U.S.- registered
               Action                      Work hours        rate  per hour     Cost per airplane             airplanes                 Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2008-17- 20....................             $80  $1,600 per inspection   11.........................  $17,600 per inspection
 10).                                                                         cycle.                                               cycle.
Inspections (new required action)..  20 to 30, depending on              80  $1,600 to $2,400 per    Up to 13...................  Up to $31,200 per
                                      group.                                  inspection cycle.                                    inspection 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 39-15648 (73 FR 50703, August 28, 2008) and by 
adding the following new airworthiness directive (AD):


[[Page 46333]]


2009-18-10 Boeing: Amendment 39-16006. Docket No. FAA-2009-0476; 
Directorate Identifier 2008-NM-188-AD.

Effective Date

    (a) This AD becomes effective October 14, 2009.

Affected ADs

    (b) This AD supersedes AD 2008-17-10, amendment 39-15648.

Applicability

    (c) This AD applies to Boeing Model 707-100 long body, -200, -
100B long body, and -100B short body series airplanes; Model 707-
300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B 
series airplanes; certificated in any category; as identified in 
Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 
18, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD results from new findings of cracks found in the 
wing to body terminal fittings during routine inspections. We are 
issuing this AD to detect and correct cracks and corrosion in the 
body terminal fittings above and below the floor, which could cause 
loss of support for the wing and could adversely affect the 
structural integrity 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.

Restatement of Requirements of AD 2008-17-10 With Updated Service 
Information

Inspections and Corrective Actions

    (g) For airplanes identified in Boeing 707 Special Attention 
Service Bulletin 3524, dated July 18, 2007: Within 24 months after 
October 2, 2008 (the effective date of AD 2008-17-10), do detailed 
inspections and applicable related investigative and corrective 
actions, by accomplishing all the actions specified in the 
Accomplishment Instructions of Boeing 707 Special Attention Service 
Bulletin 3524, dated July 18, 2007; or Boeing 707 Alert Service 
Bulletin A3524, Revision 1, dated September 18, 2008; except as 
provided by paragraph (h) of this AD. After the effective date of 
this AD, use only Boeing 707 Alert Service Bulletin A3524, Revision 
1, dated September 18, 2008. Repeat the detailed inspections 
thereafter at intervals not to exceed 24 months. Do all applicable 
related investigative and corrective actions before further flight.
    (h) If any crack or corrosion is found during any inspection 
required by paragraph (g) of this AD, and Boeing 707 Special 
Attention Service Bulletin 3524, dated July 18, 2007, or Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 
specifies to contact Boeing for appropriate action: Before further 
flight, repair the terminal fittings using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

No Information Submission

    (i) Although Boeing 707 Special Attention Service Bulletin 3524, 
dated July 18, 2007; and Boeing 707 Alert Service Bulletin A3524, 
Revision 1, dated September 18, 2008; specify to submit information 
to the manufacturer, this AD does not include that requirement.

New Requirements of This AD

Inspections

    (j) For Group 1 and Group 2 airplanes identified in Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 
on which a modification or repair was done in accordance with Boeing 
707/720 Service Bulletin 2912, Revision 1, dated March 13, 1970: At 
the later of the times specified in paragraphs (j)(1) and (j)(2) of 
this AD, do an ultrasonic inspection to detect any stress corrosion 
cracks within the outboard flange of the left and right body 
terminal fittings at body station (STA) 820, and all applicable 
related investigative and corrective actions, by accomplishing all 
the actions specified in the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3524, Revision 1, dated September 18, 
2008, except as provided by paragraph (m) of this AD. Repeat the 
ultrasonic inspection thereafter at intervals not to exceed 24 
months or 2,000 flight cycles, whichever occurs first. Do all 
applicable related investigative and corrective actions before 
further flight.
    (1) Within 24 months or 2,000 flight cycles after the effective 
date of this AD, whichever occurs first.
    (2) Within 24 months or 2,000 flight cycles after doing the 
repair or modification, whichever occurs first.
    (k) For Group 3 and Group 4 airplanes identified in Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008: 
Within 2,000 flight cycles or 24 months after the effective date of 
this AD, whichever occurs first, do an ultrasonic inspection to 
detect any stress corrosion cracks within the outboard flange of the 
left and right body terminal fittings at STA 820, and all applicable 
corrective actions, by accomplishing all the actions specified in 
the Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3524, Revision 1, dated September 18, 2008, except as provided by 
paragraph (m) of this AD. Repeat the ultrasonic inspection 
thereafter at intervals not to exceed 24 months or 2,000 flight 
cycles, whichever occurs first. Do all applicable corrective actions 
before further flight.
    (l) For Group 4 airplanes identified in Boeing 707 Alert Service 
Bulletin A3524, Revision 1, dated September 18, 2008: Within 24 
months after the effective date of this AD, do detailed inspections 
for corrosion and cracking of the body terminal fittings at STA 820, 
and all applicable related investigative and corrective actions, by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3524, Revision 1, 
dated September 18, 2008, except as provided by paragraph (m) of 
this AD. Repeat the detailed inspections thereafter at intervals not 
to exceed 24 months. Do all applicable related investigative and 
corrective actions before further flight.

Exception to Certain Procedures

    (m) If any crack or corrosion is found during any inspection 
required by paragraph (j), (k), or (l) of this AD, and Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 
specifies to contact Boeing for appropriate action: Before further 
flight, repair the terminal fittings using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

    Note 1:  Boeing 707 Alert Service Bulletin A3524, Revision 1, 
dated September 18, 2008, refers to Boeing 707/720 Service Bulletin 
2912, Revision 1, dated March 13, 1970, as an additional source of 
guidance for doing certain inspections and repairs.

Optional Terminating Action

    (n) Replacing a body terminal fitting with a fitting made from 
7075-T73 material, using a method approved in accordance with the 
procedures specified in paragraph (o) of this AD, terminates the 
repetitive inspections required by this AD for that fitting only.

Alternative Methods of Compliance (AMOCs)

    (o)(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; or, e-mail information 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 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.

Material Incorporated by Reference

    (p) You must use Boeing 707 Alert Service Bulletin A3524, 
Revision 1, dated September 18, 2008, 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

[[Page 46334]]

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 
me.boecom@boeing.com; 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 or 425-227-1152.
    (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 NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on August 18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20838 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P
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