Airworthiness Directives; The Boeing Company Airplanes, 27315-27318 [2013-11168]

Download as PDF Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 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. We prepared a regulatory evaluation of the estimated costs to comply with this proposed 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. 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 AD: rmajette on DSK2TPTVN1PROD with PROPOSALS-1 ■ Bombardier, Inc.: Docket No. FAA–2013– 0370; Directorate Identifier 2013–NM– 034–AD. (a) Comments Due Date We must receive comments by June 24, 2013. (b) Affected ADs None. VerDate Mar<15>2010 14:33 May 09, 2013 Jkt 229001 (c) Applicability This AD applies to Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10002 through 10265 inclusive; and Model CL–600– 2D15 (Regional Jet Series 705) and CL–600– 2D24 (Regional Jet Series 900) airplanes, serial numbers 15002 through 15153 inclusive, 15156 and 15157; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 35, Oxygen. (e) Reason This AD was prompted by a report that traces of oil could be found in the crew oxygen system due to the use of incorrect pressure testing procedures during manufacturing. We are issuing this AD to detect and correct oil contaminants, which could cause an ignition and result in a fire in the oxygen system. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Actions Within 6,600 flight hours or 36 months after the effective date of this AD, whichever occurs first: Clean the crew oxygen system, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–35–012, Revision A, dated November 26, 2012. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 670BA–35–012, dated August 3, 2012, which is not incorporated by reference. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7300; fax 516–794–5531. 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. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 27315 are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–01, dated January 22, 2013, and Bombardier Service Bulletin 670BA–35–012, Revision A, dated November 26, 2012, for related information. Issued in Renton, Washington, on May 2, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–11169 Filed 5–9–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0369; Directorate Identifier 2012–NM–128–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This proposed AD was prompted by reports of fractured rudder pedal pushrod connecting bolts in a rudder pedal assembly. This proposed AD would require repetitive replacements of the rudder pedal pushrod connecting bolts and repetitive inspections of the rudder pedal assembly bolt holes in each of the captain and the first officer rudder pedal assemblies, and if necessary, repair or replacement of worn rudder pedal assemblies. We are proposing this AD to prevent fracture of the rudder pedal pushrod connecting bolts during pedal use, which could result in a large involuntary input to the rudder, nose-wheel steering, and braking systems, leading to a runway excursion. DATES: We must receive comments on this proposed AD by June 24, 2013. 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. SUMMARY: E:\FR\FM\10MYP1.SGM 10MYP1 27316 Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules • 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, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; 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. 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: Marie Hogestad, Aerospace Engineer, Systems and Equipment Branch, FAA, ANM–130S, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6418; fax: 425–917– 6590; email: marie.hogestad@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited rmajette on DSK2TPTVN1PROD with PROPOSALS-1 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– 2013–0369; Directorate Identifier 2012– VerDate Mar<15>2010 14:33 May 09, 2013 Jkt 229001 NM–128–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 received reports of fractured rudder pedal pushrod connecting bolts on Boeing Model 757 airplanes. One operator discovered a bolt was fractured during an inspection, following a report that the captain’s right pedal was loose. Another operator reported a fractured bolt during the airplane pushback. When the captain applied the brakes, the right hand rudder pedal collapsed and both pedals fell forward. An inspection revealed that a rudder pedal pushrod bolt was fractured, resulting in a full left rudder input. Also, in a separate incident, during routine maintenance, while the brakes were released, a loud crack was heard and the right hand rudder pedal went all the way forward. During investigation, it was determined that the captain’s right hand rudder pedal pushrod bolt had fractured. The rudder pedal pushrod connecting bolt secures the rudder pedal arm to the rudder pushrod. The bolt is cantilevered in a single shear arrangement that is not capable of carrying its design load if there is looseness in the installation (bolt bending is introduced). The bolts can also rotate, due to lack of bolt clamp-up, causing additional wear. This condition, if not corrected, could result in a fracture of the rudder pedal pushrod connecting bolts during pedal use, which could result in large involuntary input to the rudder, nose-wheel steering, and braking systems, leading to a runway excursion. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Related Rulemaking We issued AD 2001–22–13, Amendment 39–12492 (66 FR 55075, November 1, 2001), for certain Model 737, 747, 757, 767, and 777 series airplanes. That AD requires replacing the rudder pedal pushrod fasteners (bolts) for the captain’s and first officer’s pedal assemblies with titanium fasteners (bolts). We have determined that titanium bolts are under-strength on Model 757 airplanes and must be replaced with Inconel bolts. Titanum bolts do, however, meet the static and fatigue requirements for the other airplane models affected by AD 2001–22–13, Amendment 39–12492 (66 FR 55075, November 1, 2001). Relevant Service Information We reviewed Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012. For information on the procedures and compliance times, see this service information at https://www.regulations.gov by searching for Docket No. FAA–2013–0369. 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. Replacements of the rudder pedal pushrod connecting bolts are done after each inspection specified in paragraph (g) of this AD, regardless of the inspection results. Some actions would terminate the requirements of AD 2001–22–13, Amendment 39–12492 (66 FR 55075, November 1, 2001), for Model 757 airplanes. Costs of Compliance We estimate that this proposed AD affects 685 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\10MYP1.SGM 10MYP1 27317 Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspect/replace bolts (Condition 1 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757– 27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012). 5 work-hours × $85 per hour = $425 per inspection cycle. $217 $642 per inspection cycle We estimate the following costs to do any necessary repairs/replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of Cost on U.S. operators $439,770 per inspection cycle. aircraft that might need these repairs/ replacements: ON-CONDITION COSTS Action Labor cost Replace rudder pedal assembly (Condition 2 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012). Repair rudder pedal assembly (Condition 3 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012). Repair rudder pedal assembly (Condition 4 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012). The on-condition costs in the table above are per rudder pedal assembly. Depending on the diamater of the holes found during the inspection, it may be necessary to replace or repair the rudder pedal assemblies. The parts cost to replace or repair the rudder pedal assemblies are not included in the estimate. It is considered ‘‘Parts & Materials Supplied by the Operator’’, which is referenced in Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. rmajette on DSK2TPTVN1PROD with PROPOSALS-1 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 VerDate Mar<15>2010 14:33 May 09, 2013 Jkt 229001 Unknown ..... $170 3 work-hours × $85 per hour = $255. Unknown ..... 255 4 work-hours × $85 per hour = $340. Unknown ..... 340 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 Frm 00010 Fmt 4702 Sfmt 4702 Cost per product 2 work-hours × $85 per hour = $170. 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. PO 00000 Parts cost 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– 2013–0369; Directorate Identifier 2012– NM–128–AD. (a) Comments Due Date We must receive comments by June 24, 2013. (b) Affected ADs Certain requirements of this AD terminate the requirements of AD 2001–22–13, Amendment 39–12492 (66 FR 55075, November 1, 2001), for Model 757 airplanes. E:\FR\FM\10MYP1.SGM 10MYP1 27318 Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules (c) Applicability This AD applies to all The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes, certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by reports of fractured rudder pedal pushrod connecting bolts in the rudder pedal assembly. We are issuing this AD to prevent fracture of the rudder pedal pushrod connecting bolts during pedal use, which could result in a large involuntary input to the rudder, nosewheel steering, and braking systems, leading to a runway excursion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (i) Parts Installation rmajette on DSK2TPTVN1PROD with PROPOSALS-1 (g) Inspection Within 60 months after the effective date of this AD, do a detailed inspection of the rudder pedal assembly bolt holes to determine the diameter, in each of the captain and the first officer rudder pedal assemblies, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012. Repeat this inspection thereafter at intervals not to exceed 15,000 flight cycles. (h) Installation Do the applicable actions specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD for each of the captain and first officer rudder pedal assemblies, based on the results of any inspection required by paragraph (g) of this AD. Accomplishment of paragraph (h)(1), (h)(2), or (h)(3) of this AD terminates the requirements of AD 2001–22–13, Amendment 39–12492 (66 FR 55075, November 1, 2001), for that Model 757 airplane only. (1) If the diameters of both holes are within 0.3120 and 0.3140 inch on the assembly, before further flight, install new rudder pedal pushrod connect bolt, washer, nut, and cotter pin, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757– 27A0153, Revision 1, dated October 29, 2012. (2) If the diameter of only one hole is greater than 0.3140 inch on the assembly, before further flight, do the actions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Install a new rudder pedal assembly, or install a bushing in the worn hole, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757– 27A0153, Revision 1, dated October 29, 2012. (ii) Install new rudder pedal pushrod connecting bolt, washer, nut, and cotter pin, VerDate Mar<15>2010 14:33 May 09, 2013 Jkt 229001 in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757– 27A0153, Revision 1, dated October 29, 2012. (3) If the diameters of both holes are greater than 0.3140 inch on the assembly, before further flight, do the actions specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) Install a new rudder pedal assembly, or install two bushings in the two worn holes, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757– 27A0153, Revision 1, dated October 29, 2012. (ii) Install new rudder pedal pushrod connecting bolt, washer, nut, and cotter pin, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757– 27A0153, Revision 1, dated October 29, 2012. As of the effective date of this AD, no person may install, in a rudder pedal assembly of any Boeing 757 airplane, a bolt having part number (P/N) BACB30NM5DK47. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if operators installed washers having part number NAS1149D0516J, NAS1149D0532J, and NAS1149D0563J, and if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012, which is not incorporated by reference in this AD, as unmodified by Boeing Alert Service Bulletin 757–27A0153, Revision 1, dated October 29, 2012. (k) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 (l) Related Information (1) For more information about this AD, contact Marie Hogestad, Aerospace Engineer, Systems and Equipment Branch, FAA, ANM– 130S, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6418; fax: 425– 917–6590; email: marie.hogestad@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, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; 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 2, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–11168 Filed 5–9–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0367; Directorate Identifier 2012–NM–177–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL–600–2D15 (Regional Jet Series 705) airplanes, and Model CL–600–2D24 (Regional Jet Series 900) airplanes. This proposed AD was prompted by a report of corrosion of the components of the main landing gear (MLG) retraction actuator found in service; the corrosion was found at the interface of the rod end and the piston, and at the bracket and related pins. This proposed AD would require inspection of the MLG retraction actuator components; corrective actions if necessary; and, for certain retraction actuators, installation of a new jam nut. We are proposing this AD to prevent disconnection of the MLG retraction actuator, which could result in extension of the MLG without damping, SUMMARY: E:\FR\FM\10MYP1.SGM 10MYP1

Agencies

[Federal Register Volume 78, Number 91 (Friday, May 10, 2013)]
[Proposed Rules]
[Pages 27315-27318]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11168]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0369; Directorate Identifier 2012-NM-128-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 757 airplanes. This proposed AD was prompted 
by reports of fractured rudder pedal pushrod connecting bolts in a 
rudder pedal assembly. This proposed AD would require repetitive 
replacements of the rudder pedal pushrod connecting bolts and 
repetitive inspections of the rudder pedal assembly bolt holes in each 
of the captain and the first officer rudder pedal assemblies, and if 
necessary, repair or replacement of worn rudder pedal assemblies. We 
are proposing this AD to prevent fracture of the rudder pedal pushrod 
connecting bolts during pedal use, which could result in a large 
involuntary input to the rudder, nose-wheel steering, and braking 
systems, leading to a runway excursion.

DATES: We must receive comments on this proposed AD by June 24, 2013.

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.

[[Page 27316]]

     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, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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.

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: Marie Hogestad, Aerospace Engineer, 
Systems and Equipment Branch, FAA, ANM-130S, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; phone: 425-917-6418; fax: 425-917-6590; email: 
marie.hogestad@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-2013-0369; 
Directorate Identifier 2012-NM-128-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 received reports of fractured rudder pedal pushrod connecting 
bolts on Boeing Model 757 airplanes. One operator discovered a bolt was 
fractured during an inspection, following a report that the captain's 
right pedal was loose. Another operator reported a fractured bolt 
during the airplane pushback. When the captain applied the brakes, the 
right hand rudder pedal collapsed and both pedals fell forward. An 
inspection revealed that a rudder pedal pushrod bolt was fractured, 
resulting in a full left rudder input. Also, in a separate incident, 
during routine maintenance, while the brakes were released, a loud 
crack was heard and the right hand rudder pedal went all the way 
forward. During investigation, it was determined that the captain's 
right hand rudder pedal pushrod bolt had fractured. The rudder pedal 
pushrod connecting bolt secures the rudder pedal arm to the rudder 
pushrod. The bolt is cantilevered in a single shear arrangement that is 
not capable of carrying its design load if there is looseness in the 
installation (bolt bending is introduced). The bolts can also rotate, 
due to lack of bolt clamp-up, causing additional wear. This condition, 
if not corrected, could result in a fracture of the rudder pedal 
pushrod connecting bolts during pedal use, which could result in large 
involuntary input to the rudder, nose-wheel steering, and braking 
systems, leading to a runway excursion.

Related Rulemaking

    We issued AD 2001-22-13, Amendment 39-12492 (66 FR 55075, November 
1, 2001), for certain Model 737, 747, 757, 767, and 777 series 
airplanes. That AD requires replacing the rudder pedal pushrod 
fasteners (bolts) for the captain's and first officer's pedal 
assemblies with titanium fasteners (bolts).
    We have determined that titanium bolts are under-strength on Model 
757 airplanes and must be replaced with Inconel bolts. Titanum bolts 
do, however, meet the static and fatigue requirements for the other 
airplane models affected by AD 2001-22-13, Amendment 39-12492 (66 FR 
55075, November 1, 2001).

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 757-27A0153, dated May 9, 
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 
1, dated October 29, 2012. For information on the procedures and 
compliance times, see this service information at https://www.regulations.gov by searching for Docket No. FAA-2013-0369.

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. Replacements of the 
rudder pedal pushrod connecting bolts are done after each inspection 
specified in paragraph (g) of this AD, regardless of the inspection 
results. Some actions would terminate the requirements of AD 2001-22-
13, Amendment 39-12492 (66 FR 55075, November 1, 2001), for Model 757 
airplanes.

Costs of Compliance

    We estimate that this proposed AD affects 685 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 27317]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspect/replace bolts (Condition  5 work-hours x $85             $217   $642 per inspection  $439,770 per
 1 in the Accomplishment           per hour = $425                       cycle.               inspection cycle.
 Instructions of Boeing Alert      per inspection
 Service Bulletin 757-27A0153,     cycle.
 dated May 9, 2012, as revised
 by Boeing Alert Service
 Bulletin 757-27A0153, Revision
 1, dated October 29, 2012).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs/
replacements 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/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                     Action                            Labor cost               Parts cost            product
----------------------------------------------------------------------------------------------------------------
Replace rudder pedal assembly (Condition 2 in    2 work-hours x $85 per  Unknown................            $170
 the Accomplishment Instructions of Boeing        hour = $170.
 Alert Service Bulletin 757-27A0153, dated May
 9, 2012, as revised by Boeing Alert Service
 Bulletin 757-27A0153, Revision 1, dated
 October 29, 2012).
Repair rudder pedal assembly (Condition 3 in     3 work-hours x $85 per  Unknown................             255
 the Accomplishment Instructions of Boeing        hour = $255.
 Alert Service Bulletin 757-27A0153, dated May
 9, 2012, as revised by Boeing Alert Service
 Bulletin 757-27A0153, Revision 1, dated
 October 29, 2012).
Repair rudder pedal assembly (Condition 4 in     4 work-hours x $85 per  Unknown................             340
 the Accomplishment Instructions of Boeing        hour = $340.
 Alert Service Bulletin 757-27A0153, dated May
 9, 2012, as revised by Boeing Alert Service
 Bulletin 757-27A0153, Revision 1, dated
 October 29, 2012).
----------------------------------------------------------------------------------------------------------------

    The on-condition costs in the table above are per rudder pedal 
assembly. Depending on the diamater of the holes found during the 
inspection, it may be necessary to replace or repair the rudder pedal 
assemblies. The parts cost to replace or repair the rudder pedal 
assemblies are not included in the estimate. It is considered ``Parts & 
Materials Supplied by the Operator'', which is referenced in Boeing 
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by 
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29, 2012.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2013-0369; Directorate Identifier 
2012-NM-128-AD.

(a) Comments Due Date

    We must receive comments by June 24, 2013.

(b) Affected ADs

    Certain requirements of this AD terminate the requirements of AD 
2001-22-13, Amendment 39-12492 (66 FR 55075, November 1, 2001), for 
Model 757 airplanes.

[[Page 27318]]

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF, 
-200CB, and -300 series airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    This AD was prompted by reports of fractured rudder pedal 
pushrod connecting bolts in the rudder pedal assembly. We are 
issuing this AD to prevent fracture of the rudder pedal pushrod 
connecting bolts during pedal use, which could result in a large 
involuntary input to the rudder, nose-wheel steering, and braking 
systems, leading to a runway excursion.

(f) Compliance

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

(g) Inspection

    Within 60 months after the effective date of this AD, do a 
detailed inspection of the rudder pedal assembly bolt holes to 
determine the diameter, in each of the captain and the first officer 
rudder pedal assemblies, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012. Repeat this inspection 
thereafter at intervals not to exceed 15,000 flight cycles.

(h) Installation

    Do the applicable actions specified in paragraph (h)(1), (h)(2), 
or (h)(3) of this AD for each of the captain and first officer 
rudder pedal assemblies, based on the results of any inspection 
required by paragraph (g) of this AD. Accomplishment of paragraph 
(h)(1), (h)(2), or (h)(3) of this AD terminates the requirements of 
AD 2001-22-13, Amendment 39-12492 (66 FR 55075, November 1, 2001), 
for that Model 757 airplane only.
    (1) If the diameters of both holes are within 0.3120 and 0.3140 
inch on the assembly, before further flight, install new rudder 
pedal pushrod connect bolt, washer, nut, and cotter pin, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by 
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29, 2012.
    (2) If the diameter of only one hole is greater than 0.3140 inch 
on the assembly, before further flight, do the actions specified in 
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Install a new rudder pedal assembly, or install a bushing in 
the worn hole, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as 
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, 
dated October 29, 2012.
    (ii) Install new rudder pedal pushrod connecting bolt, washer, 
nut, and cotter pin, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.
    (3) If the diameters of both holes are greater than 0.3140 inch 
on the assembly, before further flight, do the actions specified in 
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
    (i) Install a new rudder pedal assembly, or install two bushings 
in the two worn holes, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.
    (ii) Install new rudder pedal pushrod connecting bolt, washer, 
nut, and cotter pin, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.

(i) Parts Installation

    As of the effective date of this AD, no person may install, in a 
rudder pedal assembly of any Boeing 757 airplane, a bolt having part 
number (P/N) BACB30NM5DK47.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if operators installed washers 
having part number NAS1149D0516J, NAS1149D0532J, and NAS1149D0563J, 
and if those actions were performed before the effective date of 
this AD using Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, which is not incorporated by reference in this AD, as 
unmodified by Boeing Alert Service Bulletin 757-27A0153, Revision 1, 
dated October 29, 2012.

(k) 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-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, 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.

(l) Related Information

    (1) For more information about this AD, contact Marie Hogestad, 
Aerospace Engineer, Systems and Equipment Branch, FAA, ANM-130S, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; phone: 425-917-6418; fax: 425-917-6590; 
email: marie.hogestad@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, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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 2, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2013-11168 Filed 5-9-13; 8:45 am]
BILLING CODE 4910-13-P
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