Airworthiness Directives; The Boeing Company Airplanes, 31762-31765 [2012-13039]

Download as PDF 31762 Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2005–07–20, Amendment 39–14045 (70 FR 17603, April 7, 2005), and adding the following new AD. The Boeing Company: Docket No. FAA– 2010–0856; Directorate Identifier 2010– NM–117–AD. (a) Comments Due Date We must receive comments by July 16, 2012. (b) Affected ADs This AD supersedes AD 2005–07–20, Amendment 39–14045 (70 FR 17603, April 7, 2005). (c) Applicability This AD applies to The Boeing Company Model 737–600, –700, –700C, –800, and –900 series airplanes, delivered with the Rockwell Collins Enhanced Digital Flight Control System (EDFCS), certificated in any category; as identified in the Variable Number table in Section 1.A., Effectivity, of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010. Note 1 to paragraph (c) of this AD: This AD is applicable to all airplanes listed in the Variable Number table, and is not defined by the ‘‘Group 1’’ description in Section 1.A. of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010. srobinson on DSK4SPTVN1PROD with PROPOSALS (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 22, Auto Flight. (e) Unsafe Condition This AD was prompted by reports of undetected erroneous output from a single radio altimeter channel, which resulted in premature autothrottle retard during approach. We are issuing this AD to detect and correct an unsafe condition associated with erroneous output from a radio altimeter channel, which could result in premature autothrottle landing flare retard and the loss of automatic speed control, and consequent loss of control of the airplane. VerDate Mar<15>2010 16:32 May 29, 2012 Jkt 226001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Actions With No Changes This paragraph restates the actions required by paragraph (f) of AD 2005–07–20, Amendment 39–14045 (70 FR 17603, April 7, 2005). For airplanes identified in Boeing Alert Service Bulletin 737–22A1164, dated May 20, 2004: Within 12 months after May 12, 2005 (the effective date of AD 2005–07– 20, Amendment 39–14045 (70 FR 17603, April 7, 2005)), install and test an updated version of the operational program software (OPS) of the EDFCS flight control computers (FCCs), in accordance with Boeing Alert Service Bulletin 737–22A1164, dated May 20, 2004. (h) New Requirements Within 3 months after the effective date of this AD: Inspect to determine the part number of the OPS of the FCCs, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010. Installing software as required by paragraph (h)(1) of this AD, or verifying that the software is installed as specified by paragraph (h)(2) of this AD, terminates the requirements of paragraph (g) of this AD. (1) For any OPS having a part number identified in table 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010: Before further flight, install software specified in table 2 of Boeing Alert Service Bulletin 737– 22A1211, dated April 13, 2010, or install software that is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) after April 13, 2010, that is fully interchangeable with the software specified in table 2 of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010. Do the installation in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010. (2) For any OPS having a part number identified in table 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–22A1211, dated April 13, 2010: No further action is required by this paragraph. (i) Alternative Methods of Compliance (AMOCs) (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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 (3) AMOCs approved previously in accordance with AD 2005–07–20, Amendment 39–14045 (70 FR 17603, April 7, 2005), are approved as AMOCs for the corresponding provisions of this AD. (j) Related Information (1) For more information about this AD, contact Gregg Nesemeier, Senior Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6479; fax: (425) 917–6590; email: gregg.nesemeier@faa.gov. (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; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057–3356. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 21, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–13028 Filed 5–29–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0490; Directorate Identifier 2012–NM–066–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Notice of proposed rulemaking (NPRM). ACTION: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This proposed AD was prompted by reports of cracking of the midspar fittings, and of the engine and nacelle strut separating from the airplane. This proposed AD would require performing a detailed inspection of the midspar fittings of the nacelle strut to confirm that the correct part number is installed, and installing the correct part number if necessary; performing repetitive high frequency eddy current inspections (HFEC) of the midspar fittings of the nacelle strut for cracks, and repair if necessary; and SUMMARY: E:\FR\FM\30MYP1.SGM 30MYP1 Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules performing repetitive general visual inspections of the nacelle struts to verify that the nacelle strut has not drooped below its normal position, applying the droop stripe to the nacelle strut and sailboat fairing if necessary, and repair if necessary. We are proposing this AD to detect and correct cracking of the midspar fitting, which could result in separation of the nacelle strut and engine from the airplane while in flight, and consequent loss of controllability of the airplane. DATES: We must receive comments on this proposed AD by July 16, 2012. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. srobinson on DSK4SPTVN1PROD with PROPOSALS 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, VerDate Mar<15>2010 16:32 May 29, 2012 Jkt 226001 165501 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917–6577; fax: (425) 917–6590; email: Berhane.Alazar@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2012–0490; Directorate Identifier 2012– NM–066–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of fatigue cracking of the midspar fittings, and the engine and nacelle strut separating from the airplane. Operators have reported that the cracking occurred on more than 40 airplanes with approximately 9,900 to 63,000 flight hours. In addition, there has been a report of the engine number 3 nacelle strut separating from the airplane and contacting the engine number 4 nacelle strut, which also separated from the airplane. This condition, if not corrected, could result in a fractured midspar fitting, which could cause a separation of the nacelle strut and engine from the airplane while in flight, resulting in loss of controllability of the airplane. Relevant Service Information We reviewed Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. That service information describes procedures for: • Performing a detailed inspection of the midspar fittings of the engine number 2 and 3 nacelle struts to confirm that the correct part number is installed, and installing the correct part number if necessary. • Performing HFEC inspections of the midspar fittings of the engine number 2 and 3 nacelle struts for cracks, and repairing if necessary. • Performing repetitive general visual inspections of the nacelle struts of engine numbers 1, 2, 3, and 4 to verify that the nacelle strut has not drooped PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 31763 below its normal position, applying the droop stripe to the nacelle strut and sailboat fairing if necessary, and repairing if necessary. The initial compliance times for the HFEC and general visual inspections, and the application of the droop stripe if necessary, is at the later of: (1) Within 1,500 flight cycles or 48 months from the replacement of the nacelle strut inboard and outboard midspar fittings, whichever occurs first, or (2) within 120 days. For the HFEC inspection, the repetitive interval is within 250 flight cycles or 12 months, whichever occurs first. For the general visual inspection, the repetitive interval is 30 flight cycles, except after both midspar fittings are replaced on the strut, the next inspection would be performed within 1,500 flight cycles or 48 months, whichever occurs first, from the replacement of both the nacelle strut inboard and outboard midspar fittings. Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, refers to Boeing 707/720 Service Bulletin 3183, Revision 5, dated September 16, 1993, as an additional source of guidance for the HFEC inspections of the midspar fittings of the engine number 2 and 3 nacelle struts for cracks. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Information.’’ Differences Between the Proposed AD and the Service Information Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. E:\FR\FM\30MYP1.SGM 30MYP1 31764 Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, refers to ‘‘Manual 707, 720 NDT Part 6, 51–00– 00 Figure 24 as an accepted procedure’’ for the HFEC inspection. This proposed AD would require that the inspection must be done in accordance with Subject 51–00–00 Figure 24, Steel Part Surface Inspection (Impedance Plane Display), of Part 6, Eddy Current, of the Boeing 707, 720 Nondestructive Test Manual, Document D6–48023, Revision 120, dated March 15, 2012. Costs of Compliance We estimate that this proposed AD affects 11 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Detailed inspection, repetitive HFEC inspections and repetitive general visual inspections of the midspar fittings of the nacelle strut. 23 work-hours × $85 per hour = $1,955 $0 $1,955 $21,505 We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Action 130 work-hours × $85 per hour = $11,050 Install the correct part number 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. srobinson on DSK4SPTVN1PROD with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, VerDate Mar<15>2010 16:32 May 29, 2012 Parts cost Cost per product $7,867 × 4 = $31,468 ......... $42,518 Labor cost Jkt 226001 (2) Is not a ‘‘significant rule’’ under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2012–0490; Directorate Identifier 2012– NM–066–AD. (a) Comments Due Date We must receive comments by July 16, 2012. PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company 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. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. (e) Unsafe Condition This AD was prompted by reports of cracking of the midspar fittings and of the engine and nacelle strut separating from the airplane. We are issuing this AD to detect and correct cracking of the midspar fitting, which could result in separation of the nacelle strut and engine from the airplane while in flight, and consequent loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Detailed Inspection Within 120 days after the effective date of this AD: Do a detailed inspection of the midspar fittings of the engine number 2 and 3 nacelle struts to confirm that the correct part number is installed, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. If any incorrect part number is found: Before further flight, install the correct part number, in accordance with the Accomplishment Instructions of Boeing E:\FR\FM\30MYP1.SGM 30MYP1 Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules 707 Alert Service Bulletin A3537, dated January 30, 2012. Note 1 to paragraph (g) of this AD: Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, refers to Boeing 707/720 Service Bulletin 3183, Revision 5, dated September 16, 1993, as an additional source of guidance for high frequency eddy current inspections of the midspar fittings of the engine number 2 and 3 nacelle struts for cracks. srobinson on DSK4SPTVN1PROD with PROPOSALS (h) High Frequency Eddy Current Inspection (HFEC) At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, except as provided in paragraph (j) of this AD: Do an HFEC inspection of the midspar fittings of the engine number 2 and 3 nacelle struts for cracks, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, except as provided by paragraph (k) of this AD. If any crack is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Thereafter, repeat the inspection at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. (i) General Visual Inspection of the Nacelle Struts of Engine Numbers 1, 2, 3, and 4 At the applicable times in paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, except as provided in paragraph (j) of this AD: Do a general visual inspection of the nacelle struts of engine numbers 1, 2, 3, and 4 to verify that the nacelle strut has not drooped below its normal position, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. Thereafter, repeat the inspection at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. (1) If any nacelle strut has drooped below its normal position: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (2) If any nacelle strut has not drooped below its normal position, and no droop stripe has been applied, as specified in Boeing 707/720 Service Bulletin 3377, dated November 21, 1979: At the applicable times in paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, except as provided in paragraph (j) of this AD: Apply the droop stripe to the nacelle strut and sailboat fairing, on each side of the engine numbers 1, 2, 3, and 4 nacelle struts, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. (j) Exception to the Compliance Time Where Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, specifies a VerDate Mar<15>2010 16:32 May 29, 2012 Jkt 226001 31765 compliance time based on ‘‘the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. 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. (k) Exception to the Service Information Where Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, refers to ‘‘Manual 707, 720 NDT Part 6, 51–00–00 Figure 24 as an accepted procedure’’ for the HFEC inspection, this AD requires that the inspection must be done in accordance with Subject 51–00–00 Figure 24, Steel Part Surface Inspection (Impedance Plane Display), of Part 6, Eddy Current, of the Boeing 707, 720 Nondestructive Test Manual, Document D6–48023, Revision 120, dated March 15, 2012. Issued in Renton, Washington, on May 21, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (l) Credit for Previous Actions This paragraph provides credit for the installation of the engine droop lines required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Boeing 707/720 Service Bulletin 3377, dated November 21, 1979. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), ANM–120S, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ 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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, ANM–120S 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. [FR Doc. 2012–13039 Filed 5–29–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE Minority Business Development Agency 15 CFR Part 1400 [Docket No. 120517080–2080–01] Petition for Inclusion of the ArabAmerican Community in the Groups Eligible for MBDA Services Minority Business Development Agency, Commerce. ACTION: Notice of proposed rulemaking and request for comments. AGENCY: The Minority Business Development Agency (MBDA) publishes this notice regarding the petition received on January 11, 2012 from the American-Arab Anti-Discrimination Committee (ADC) requesting formal designation of Arab-Americans as a minority group that is socially or economically disadvantaged pursuant to 15 CFR art 1400. The formal designation of the Arab-American community as a group that is socially or economically disadvantaged would allow the members of this community to receive assistance from MBDA funded programs, such as the MBDA Business Center program. The ADC filed a petition, pursuant to 15 CFR part 1400.3, including information specifically related to social and economic discrimination against ArabAmericans. This Notice provides public (n) Related Information notice that the United States Department of Commerce (Department) (1) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, will consider the petition and requests Airframe Branch, ANM–120S, FAA, Seattle public comment on the propriety of this Aircraft Certification Office, 1601 Lind designation. MBDA will make a Avenue SW., Renton, WA 98057–3356; decision on the application no later than phone: (425) 917–6577; fax: (425) 917–6590; June 27, 2012. email: Berhane.Alazar@faa.gov. DATES: Comments must be received by (2) For service information identified in this AD, contact Boeing Commercial MBDA no later than June 29, 2012. Airplanes, Attention: Data & Services ADDRESSES: You may submit comments, Management, P.O. Box 3707, MC 2H–65, identified with Docket No. 120517080– Seattle, Washington 98124–2207; telephone 2080–01, using any of the following 206–544–5000, extension 1; fax 206–766– 5680; email me.boecom@boeing.com; Internet methods: • Mail, Hand/Delivery/Courier: Ms. https://www.myboeingfleet.com. You may review copies of the referenced service Josephine Arnold, Chief Counsel, PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 SUMMARY: E:\FR\FM\30MYP1.SGM 30MYP1

Agencies

[Federal Register Volume 77, Number 104 (Wednesday, May 30, 2012)]
[Proposed Rules]
[Pages 31762-31765]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-13039]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0490; Directorate Identifier 2012-NM-066-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 707 airplanes, and Model 720 and 720B series 
airplanes. This proposed AD was prompted by reports of cracking of the 
midspar fittings, and of the engine and nacelle strut separating from 
the airplane. This proposed AD would require performing a detailed 
inspection of the midspar fittings of the nacelle strut to confirm that 
the correct part number is installed, and installing the correct part 
number if necessary; performing repetitive high frequency eddy current 
inspections (HFEC) of the midspar fittings of the nacelle strut for 
cracks, and repair if necessary; and

[[Page 31763]]

performing repetitive general visual inspections of the nacelle struts 
to verify that the nacelle strut has not drooped below its normal 
position, applying the droop stripe to the nacelle strut and sailboat 
fairing if necessary, and repair if necessary. We are proposing this AD 
to detect and correct cracking of the midspar fitting, which could 
result in separation of the nacelle strut and engine from the airplane 
while in flight, and consequent loss of controllability of the 
airplane.

DATES: We must receive comments on this proposed AD by July 16, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; email me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
165501 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6577; 
fax: (425) 917-6590; email: Berhane.Alazar@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2012-0490; 
Directorate Identifier 2012-NM-066-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of fatigue cracking of the midspar 
fittings, and the engine and nacelle strut separating from the 
airplane. Operators have reported that the cracking occurred on more 
than 40 airplanes with approximately 9,900 to 63,000 flight hours. In 
addition, there has been a report of the engine number 3 nacelle strut 
separating from the airplane and contacting the engine number 4 nacelle 
strut, which also separated from the airplane. This condition, if not 
corrected, could result in a fractured midspar fitting, which could 
cause a separation of the nacelle strut and engine from the airplane 
while in flight, resulting in loss of controllability of the airplane.

Relevant Service Information

    We reviewed Boeing 707 Alert Service Bulletin A3537, dated January 
30, 2012. That service information describes procedures for:
     Performing a detailed inspection of the midspar fittings 
of the engine number 2 and 3 nacelle struts to confirm that the correct 
part number is installed, and installing the correct part number if 
necessary.
     Performing HFEC inspections of the midspar fittings of the 
engine number 2 and 3 nacelle struts for cracks, and repairing if 
necessary.
     Performing repetitive general visual inspections of the 
nacelle struts of engine numbers 1, 2, 3, and 4 to verify that the 
nacelle strut has not drooped below its normal position, applying the 
droop stripe to the nacelle strut and sailboat fairing if necessary, 
and repairing if necessary.
    The initial compliance times for the HFEC and general visual 
inspections, and the application of the droop stripe if necessary, is 
at the later of: (1) Within 1,500 flight cycles or 48 months from the 
replacement of the nacelle strut inboard and outboard midspar fittings, 
whichever occurs first, or (2) within 120 days.
    For the HFEC inspection, the repetitive interval is within 250 
flight cycles or 12 months, whichever occurs first.
    For the general visual inspection, the repetitive interval is 30 
flight cycles, except after both midspar fittings are replaced on the 
strut, the next inspection would be performed within 1,500 flight 
cycles or 48 months, whichever occurs first, from the replacement of 
both the nacelle strut inboard and outboard midspar fittings.
    Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, 
refers to Boeing 707/720 Service Bulletin 3183, Revision 5, dated 
September 16, 1993, as an additional source of guidance for the HFEC 
inspections of the midspar fittings of the engine number 2 and 3 
nacelle struts for cracks.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''

Differences Between the Proposed AD and the Service Information

    Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, 
specifies to contact the manufacturer for instructions on how to repair 
certain conditions, but this proposed AD would require repairing those 
conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

[[Page 31764]]

    Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, 
refers to ``Manual 707, 720 NDT Part 6, 51-00-00 Figure 24 as an 
accepted procedure'' for the HFEC inspection. This proposed AD would 
require that the inspection must be done in accordance with Subject 51-
00-00 Figure 24, Steel Part Surface Inspection (Impedance Plane 
Display), of Part 6, Eddy Current, of the Boeing 707, 720 
Nondestructive Test Manual, Document D6-48023, Revision 120, dated 
March 15, 2012.

Costs of Compliance

    We estimate that this proposed AD affects 11 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Detailed inspection, repetitive HFEC  23 work-hours x $85 per              $0           $1,955          $21,505
 inspections and repetitive general    hour = $1,955
 visual inspections of the midspar
 fittings of the nacelle strut.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
              Action                    Labor cost                     Parts cost                    product
----------------------------------------------------------------------------------------------------------------
Install the correct part number    130 work-hours x $85  $7,867 x 4 = $31,468..................         $42,518
                                    per hour = $11,050
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (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.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2012-0490; Directorate Identifier 
2012-NM-066-AD.

(a) Comments Due Date

    We must receive comments by July 16, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company 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.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 54, Nacelles/Pylons.

(e) Unsafe Condition

    This AD was prompted by reports of cracking of the midspar 
fittings and of the engine and nacelle strut separating from the 
airplane. We are issuing this AD to detect and correct cracking of 
the midspar fitting, which could result in separation of the nacelle 
strut and engine from the airplane while in flight, and consequent 
loss of controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Detailed Inspection

    Within 120 days after the effective date of this AD: Do a 
detailed inspection of the midspar fittings of the engine number 2 
and 3 nacelle struts to confirm that the correct part number is 
installed, in accordance with the Accomplishment Instructions of 
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. If 
any incorrect part number is found: Before further flight, install 
the correct part number, in accordance with the Accomplishment 
Instructions of Boeing

[[Page 31765]]

707 Alert Service Bulletin A3537, dated January 30, 2012.

    Note 1 to paragraph (g) of this AD:  Boeing 707 Alert Service 
Bulletin A3537, dated January 30, 2012, refers to Boeing 707/720 
Service Bulletin 3183, Revision 5, dated September 16, 1993, as an 
additional source of guidance for high frequency eddy current 
inspections of the midspar fittings of the engine number 2 and 3 
nacelle struts for cracks.

(h) High Frequency Eddy Current Inspection (HFEC)

    At the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012, except as provided in paragraph (j) of this AD: Do 
an HFEC inspection of the midspar fittings of the engine number 2 
and 3 nacelle struts for cracks, in accordance with the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3537, dated January 30, 2012, except as provided by paragraph (k) 
of this AD. If any crack is found, before further flight, repair 
using a method approved in accordance with the procedures specified 
in paragraph (m) of this AD. Thereafter, repeat the inspection at 
the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012.

(i) General Visual Inspection of the Nacelle Struts of Engine Numbers 
1, 2, 3, and 4

    At the applicable times in paragraph 1.E., ``Compliance,'' of 
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012, 
except as provided in paragraph (j) of this AD: Do a general visual 
inspection of the nacelle struts of engine numbers 1, 2, 3, and 4 to 
verify that the nacelle strut has not drooped below its normal 
position, in accordance with the Accomplishment Instructions of 
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012. 
Thereafter, repeat the inspection at the applicable intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing 707 Alert 
Service Bulletin A3537, dated January 30, 2012.
    (1) If any nacelle strut has drooped below its normal position: 
Before further flight, repair using a method approved in accordance 
with the procedures specified in paragraph (m) of this AD.
    (2) If any nacelle strut has not drooped below its normal 
position, and no droop stripe has been applied, as specified in 
Boeing 707/720 Service Bulletin 3377, dated November 21, 1979: At 
the applicable times in paragraph 1.E., ``Compliance,'' of Boeing 
707 Alert Service Bulletin A3537, dated January 30, 2012, except as 
provided in paragraph (j) of this AD: Apply the droop stripe to the 
nacelle strut and sailboat fairing, on each side of the engine 
numbers 1, 2, 3, and 4 nacelle struts, in accordance with the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3537, dated January 30, 2012.

(j) Exception to the Compliance Time

    Where Boeing 707 Alert Service Bulletin A3537, dated January 30, 
2012, specifies a compliance time based on ``the original issue date 
of this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(k) Exception to the Service Information

    Where Boeing 707 Alert Service Bulletin A3537, dated January 30, 
2012, refers to ``Manual 707, 720 NDT Part 6, 51-00-00 Figure 24 as 
an accepted procedure'' for the HFEC inspection, this AD requires 
that the inspection must be done in accordance with Subject 51-00-00 
Figure 24, Steel Part Surface Inspection (Impedance Plane Display), 
of Part 6, Eddy Current, of the Boeing 707, 720 Nondestructive Test 
Manual, Document D6-48023, Revision 120, dated March 15, 2012.

(l) Credit for Previous Actions

    This paragraph provides credit for the installation of the 
engine droop lines required by paragraph (i) of this AD, if those 
actions were performed before the effective date of this AD using 
Boeing 707/720 Service Bulletin 3377, dated November 21, 1979.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
ANM-120S, FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, ANM-120S 
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.

(n) Related Information

    (1) 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, WA 98057-3356; 
phone: (425) 917-6577; fax: (425) 917-6590; email: 
Berhane.Alazar@faa.gov.
    (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; email 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 21, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-13039 Filed 5-29-12; 8:45 am]
BILLING CODE 4910-13-P
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