3564 Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 

engines; as identified in Boeing Alert Service 

Bulletin 777–78A0065, Revision 2, dated 

May 6, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine exhaust. 

Unsafe Condition 

(e) This AD results from reports of thrust 

reverser events related to thermal damage of 

the thrust reverser (T/R) inner wall. The 

Federal Aviation Administration is issuing 

this AD to detect and correct a degraded T/ 

R inner wall panel, which could lead to 

failure of a T/R and adjacent components and 

their consequent separation from the 

airplane, which could result in a rejected 

takeoff (RTO) and cause asymmetric thrust 

and consequent loss of control of the airplane 

during reverse thrust operation. If a T/R inner 

wall overheats, separated components could 

cause structural damage to the airplane, 

damage to other airplanes, or possible injury 

to people on the ground. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Records Review, Inspections, and Related 

Investigative and Corrective Actions 

(g) Except as required by paragraphs (h), 

(i), (j), and (k) of this AD, at the applicable 

times in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010 (‘‘this service 

bulletin’’), review the airplane maintenance 

records to determine whether sealant was 

added, do the actions specified in paragraphs 

(g)(1), (g)(2), (g)(3), (g)(4), and (g)(5) of this 

AD, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of this service bulletin, except as 

required by paragraph (l) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections required by 

paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and 

(g)(5) of this AD thereafter at the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of the service bulletin. 

(1) Do a detailed inspection of all T/R inner 

wall insulation blanket edges, grommet 

holes, penetrations, and seams for sealant 

that is cracked, has gaps, is loose, or is 

missing; do a general visual inspection of 

click bond studs, blanket studs, and 

temporary fasteners; and replace sealant as 

applicable; in accordance with Work Package 

1 of the Accomplishment Instructions of this 

service bulletin. 

(2) Do the actions required by paragraph 

(g)(2)(i) or (g)(2)(ii) of this AD. 

(i) Do a full inner wall panel nondestructive test (NDT) for delamination and 

disbonding of each T/R half, and do a general 

visual inspection for areas of thermal 

degradation, in accordance with Work 

Package 2 of the Accomplishment 

Instructions of this service bulletin. 

(ii) Do a limited area NDT of the inner wall 

panel of each T/R half for delamination and 

disbonding, and do a general visual 

inspection for areas of thermal degradation, 

in accordance with Work Package 6 of the 

Accomplishment Instructions of this service 

bulletin. 

(3) Do a general visual inspection of the T/ 

R perforated wall aft of the intermediate 

pressure compressor 8th stage (IP8) and the 

high pressure compressor 3rd stage (HP3) 

bleed port exits for a color that is different 

from that of the general area, in accordance 

with Work Package 5 of the Accomplishment 

Instructions of this service bulletin. 

(4) Do a detailed inspection of the powered 

door opening system (PDOS) lug bushings on 

the upper number 1 compression pad fittings 

for hole elongation, deformation, and contact 

with the PDOS actuator, in accordance with 

Work Package 3 of the Accomplishment 

Instructions of this service bulletin. 

(5) Do an NDT of the number 1 upper and 

numbers 1 and 2 lower compression pad 

fittings, in accordance with Work Package 4 

of the Accomplishment Instructions of this 

service bulletin. 

Exceptions to the Service Bulletin 

(h) Where Boeing Alert Service Bulletin 

777–78A0065, Revision 2, dated May 6, 2010, 

specifies a compliance time after the date on 

the original issue of that service bulletin, this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(i) Where paragraph 1.E., ‘‘Compliance,’’ in 

Boeing Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010, specifies a 

compliance time of ‘‘2,000 flight cycles after 

the date of the operator’s own inspections,’’ 

for doing Work Packages 2 and 5, or Work 

Packages 2 and 6, this AD requires 

compliance within 2,000 flight cycles after 

the date of the operator’s own inspections or 

within 12 months after the effective date of 

this AD, whichever occurs later. 

(j) Where the Condition columns in Table 

2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010, refer to ‘‘All 

airplanes, each T/R half’’ that has or has not 

‘‘been inspected before the date on this 

service bulletin,’’ this AD applies to all 

airplanes, each T/R half that has or has not 

been inspected before the effective date of 

this AD. 

(k) Where the Condition columns in the 

Tables of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010, refer to total 

flight cycles, this AD applies to the airplanes 

with the specified total flight cycles as of the 

effective date of this AD. 

(l) Where Boeing Alert Service Bulletin 

777–78A0065, Revision 2, dated May 6, 2010, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. 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. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 777–78A0065, dated June 

23, 2008; or Revision 1, dated January 29, 

2009; are acceptable for compliance with the 

corresponding requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to Attn: 

Margaret Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6500; fax (425) 

917–6590. Or, e-mail information 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. 

Issued in Renton, Washington, on January 

12, 2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–1121 Filed 1–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0042; Directorate 

Identifier 2009–NM–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Model SAAB 340A 

(SAAB/SF340A) and SAAB 340B 

Airplanes Modified in Accordance With 

Supplemental Type Certificate (STC) 

ST00224WI–D, ST00146WI–D, or 

SA984GL–D 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Saab AB, Saab Aerosystems 

Model SAAB 340A (SAAB/SF340A) and 

SAAB 340B airplanes. The first 

supplemental NPRM would have 

required inspecting the fuselage surface 

for corrosion and cracking behind the 

external adapter plate of the antennae 

installation, and repair if necessary. The 

first supplemental NPRM resulted from 

a report of a crack found behind the 

external adapter plate of the antennae 

during inspection. Similar cracking was 

found on two additional airplanes, and 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 3565 

extensive corrosion was found on one 

airplane. This action revises the first 

supplemental NPRM by correcting an 

STC number, which would expand the 

applicability of the first supplemental 

NPRM. We are proposing this second 

supplemental NPRM to detect and 

correct corrosion and cracking behind 

the external adapter plate of the 

antennae of certain damage-tolerant 

structure, which could result in reduced 

structural integrity and consequent 

rapid depressurization of the airplane. 

DATES: We must receive comments on 

this supplemental NPRM by March 7, 

2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 

67209; telephone (316) 946–4116; fax 

(316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0042; Directorate Identifier 

2009–NM–010–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 http:// 

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 issued a supplemental notice of 

proposed rulemaking (NPRM) (the ‘‘first 

supplemental NPRM’’) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Saab AB, Saab Aerosystems 

Model SAAB 340A (SAAB/SF340A) and 

SAAB 340B airplanes. That first 

supplemental NPRM was published in 

the Federal Register on August 23, 2010 

(75 FR 51696). That first supplemental 

NPRM proposed to require inspecting 

the fuselage surface for corrosion and 

cracking behind the external adapter 

plate of the antennae installation, and 

repair if necessary. 

Actions Since First Supplemental 

NPRM Was Issued 

Since we issued the first 

supplemental NPRM, we have 

determined that STC number 

SA00224WI–D, identified in the 

applicability of the first supplemental 

NPRM, is an incorrect STC number; the 

correct number is ST00224WI–D. We 

have corrected this error, which 

expands the airplanes affected by the 

first supplemental NPRM. 

Comments 

We gave the public the opportunity to 

comment on the first supplemental 

NPRM. We received no comments on 

that NPRM or on the determination of 

the cost to the public. 

FAA’s Determination and Proposed 

Requirements of the Supplemental 

NPRM 

We are proposing this second 

supplemental NPRM because we 

evaluated all pertinent information and 

determined an unsafe condition exists 

and is likely to exist or develop on other 

products of these same type designs. 

The change described above expands 

the scope of the first supplemental 

NPRM. As a result, we have determined 

that it is necessary to reopen the 

comment period to provide additional 

opportunity for the public to comment 

on this second supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This second supplemental NPRM 

would retain all the requirements in the 

first supplemental NPRM. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 201 airplanes of U.S. 

registry. The proposed inspection would 

take about 4 work hours per airplane, at 

an average labor rate of $85 per work 

hour. Based on these figures, the 

estimated cost of the proposed AD for 

U.S. operators is $68,340, or $340 per 

airplane. 

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), and 

(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 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
3566 Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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: 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2010–0042; Directorate Identifier 

2009–NM–010–AD. 

Comments Due Date 

(a) We must receive comments by March 7, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Saab AB, Saab 

Aerosystems airplanes, certificated in any 

category, identified in paragraphs (c)(1) and 

(c)(2) of this AD, that have been modified in 

accordance with Supplemental Type 

Certificate (STC) ST00224WI–D, 

ST00146WI–D, or SA984GL–D. 

(1) Model SAAB 340A (SAAB/SF340A) 

airplanes, serial numbers 004 through 159 

inclusive. 

(2) Model SAAB 340B airplanes, serial 

numbers 160 through 459 inclusive. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report of a crack 

found behind the external adapter plate of 

the antennae during inspection. Similar 

cracking was found on two additional 

airplanes, and extensive corrosion was found 

on one airplane. The Federal Aviation 

Administration is issuing this AD to detect 

and correct corrosion and cracking behind 

the external adapter plate of the antennae of 

certain damage-tolerant structure, which 

could result in reduced structural integrity 

and consequent rapid depressurization of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified. 

Inspection/Corrective Actions 

(g) Within 600 flight cycles after the 

effective date of this AD: Remove the external 

adapter plate of the antennae installation and 

do a general visual inspection of the fuselage 

surface for corrosion and cracking behind the 

external adapter plate of the antennae 

installation. If any corrosion or cracking is 

found, repair before further flight. If no 

corrosion or cracking is found, before further 

flight, ensure that proper corrosion 

protection has been applied before 

reinstalling the adapter plate. Do all the 

actions required by this paragraph in 

accordance with a method approved by the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Reporting Requirement 

(h) At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD: Submit 

a report of the positive findings of the 

inspections required by paragraph (g) of this 

AD. Send the report to the Manager, Wichita 

ACO. The report must contain, at a 

minimum, the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

flight cycles and flight hours on the airplane 

since installation of the STC. Under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(3) A Federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave., SW, Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

Special Flight Permit 

(i) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), may be issued to operate the 

airplane to a location where the requirements 

of this AD can be accomplished, but 

concurrence by the Manager, Wichita ACO, 

FAA, is required prior to issuance of the 

special flight permit. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Wichita ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, Wichita 

ACO, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; 

telephone (316) 946–4116; fax (316) 946– 

4107. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC, 

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. 

Issued in Renton, Washington on January 

12, 2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–1118 Filed 1–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0026; Directorate 

Identifier 2010–NM–104–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200 and –300 

Series Airplanes Equipped With Pratt 

and Whitney Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 777–200 and –300 series 

airplanes. This proposed AD would 

require repetitive inspections for 


emcdonald on DSK2BSOYB1PROD with PROPOSALS