46864 Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(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 

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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, 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 and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to EASA Airworthiness Directives 

2006–0225, dated July 21, 2006, and 2010– 

0048, dated March 19, 2010; Airbus A330 

Certification Maintenance Requirements, 

Document 955.2074/93, Issue 19, dated 

March 22, 2006; and Airbus A330 ALS, Part 

3—Certification Maintenance Requirements, 

Revision 02, dated December 16, 2009; for 

related information. 

Issued in Renton, Washington, on July 28, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19179 Filed 8–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0225; Directorate 

Identifier 2009–NM–203–AD] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers PLC Model SD3 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

NPRM for the products listed above. 

This action revises the earlier NPRM by 

expanding the scope. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Subsequent to accidents involving Fuel 

Tank System explosions in flight * * * and 

on ground, * * * Special Federal Aviation 

Regulation 88 (SFAR88) * * * required a 

safety review of the aircraft Fuel Tank 

System * * *. 

* * * * * 

Fuel Airworthiness Limitations are items 

arising from a systems safety analysis that 

have been shown to have failure mode(s) 

associated with an ‘unsafe condition’ * * *. 

These are identified in Failure Conditions for 

which an unacceptable probability of ignition 

risk could exist if specific tasks and/or 

practices are not performed in accordance 

with the manufacturers’ requirements. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by August 30, 2010. 

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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Short 

Brothers PLC, Airworthiness, P.O. Box 

241, Airport Road, Belfast, BT3 9DZ 

Northern Ireland; telephone 

+44(0)2890–462469; fax +44(0)2890– 

468444; e-mail michael.mulholland

@aero.bombardier.com; Internet http:// 

www.bombardier.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 http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations 

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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

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–2010–0225; Directorate Identifier 

2009–NM–203–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 based on 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 proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

March 15, 2010 (75 FR 12154). That 

earlier NPRM proposed to supersede AD 

2006–12–18, Amendment 39–14644 (71 

FR 34801, June 16, 2006), to require 

actions intended to address the unsafe 

condition for the products listed above. 

Since that NPRM was issued, we have 

determined that the original NPRM did 

not include all the relevant service 

information for the affected airplanes. 

Relevant Service Information 

Bombardier has issued the temporary 

revisions (TRs) listed in the following 

table. 


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TABLE—AMM TEMPORARY REVISIONS

Model— Shorts temporary revision— Dated— To the maintenance manual 

(MM)— 

SD3–30 airplanes ................................. TR330–AMM–35 .................................. June 6, 2006 .......................... Shorts SD3–30 MM. 

SD3–30 airplanes ................................. TR330–AMM–36 .................................. June 6, 2006 .......................... Shorts SD3–30 MM. 

SD3–SHERPA airplanes ...................... TRSD3S–AMM–36 .............................. June 19, 2006 ........................ Shorts SD3-SHERPA MM. 

SD3–SHERPA airplanes ...................... TRSD3S–AMM–37 .............................. June 19, 2006 ........................ Shorts SD3-SHERPA MM. 

SD3–60 SHERPA airplanes ................. TRSD360S–AMM–35 .......................... June 27, 2006 ........................ Shorts SD3–60 Sherpa MM. 

SD3–60 SHERPA airplanes ................. TRSD360S–AMM–36 .......................... June 27, 2006 ........................ Shorts SD3–60 Sherpa MM. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

Comments 

We have considered the following 

comments received on the earlier 

NPRM. 

Request To Include Additional Service 

Information 

Bombardier requests that we add the 

TRs specified in the previous table to 

Table 3 of the NPRM. 

We agree and have revised this 

supplemental NPRM accordingly. 

Request To Revise Costs of Compliance 

Bombardier requests that we revise 

the costs of compliance to account for 

any Model SD3–30 airplanes. 

We agree that clarification may be 

necessary. The Costs of Compliance 

section accounts for 54 U.S.-registered 

airplanes, all of which are operated as 

transport category airplanes, not 

military airplanes. 

Request To Remove Reference to 

Fuselage Pressure Shell 

Bombardier requests that we revise 

paragraph (h) of the NPRM to remove 

reference to ‘‘longitudinal skin joints in 

the fuselage pressure shell.’’ Bombardier 

notes that this statement is erroneous 

because the Model SD3 airplanes are not 

pressurized. 

We agree with the request and have 

removed ‘‘pressure’’ from the statement 

from paragraph (h) of this supplemental 

NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Certain changes described above 

expand the scope of the earlier 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 proposed AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 54 products of U.S. registry. 

The actions that are required by AD 

2006–12–18 and retained in this 

proposed AD take about 41 work-hours 

per product, at an average labor rate of 

$85 per work hour. Required parts cost 

about $10 per product. Based on these 

figures, the estimated cost of the 

currently required actions is $3,485 per 

product. 

We estimate that it would take about 

1 work-hour per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$4,590, or $85 per product. 

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 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, 


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46866 Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 

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: 

Short Brothers PLC: Docket No. FAA–2010– 

0225; Directorate Identifier 2009–NM– 

203–AD. 

Comments Due Date 

(a) We must receive comments by August 

30, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–12–18, 

Amendment 39–14644. 

Applicability 

(c) This AD applies to all Short Brothers 

PLC Model SD3–60 SHERPA, SD3–SHERPA, 

SD3–30, and SD3–60 airplanes, certificated 

in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (l) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Subsequent to accidents involving Fuel 

Tank System explosions in flight * * * and 

on ground, the FAA published Special 

Federal Aviation Regulation 88 (SFAR88) in 

June 2001. SFAR 88 required a safety review 

of the aircraft Fuel Tank System to determine 

that the design meets the requirements of 

FAR [Federal Aviation Regulation] § 25.901 

and § 25.981(a) and (b). 

A similar regulation has been 

recommended by the JAA [Joint Aviation 

Authorities] to the European National 

Aviation Authorities in JAA letter 04/00/02/ 

07/03–L024 of 3 February 2003. The review 

was requested to be mandated by NAA’s 

[National Airworthiness Authorities] using 

JAR [Joint Aviation Requirement] § 25.901(c), 

§ 25.1309. 

In August 2005 EASA [European Aviation 

Safety Agency] published a policy statement 

on the process for developing instructions for 

maintenance and inspection of Fuel Tank 

System ignition source prevention (EASA D 

2005/CPRO, http://www.easa.eu.int/home/ 

cert_policy_statements_en.html) that also 

included the EASA expectations with regard 

to compliance times of the corrective actions 

on the unsafe and the not unsafe part of the 

harmonised design review results. On a 

global scale the TC [type certificate] holders 

committed themselves to the EASA 

published compliance dates (see EASA 

policy statement). The EASA policy 

statement has been revised in March 2006: 

The date of 31–12–2005 for the unsafe related 

actions has now been set at 01–07–2006. 

Fuel Airworthiness Limitations are items 

arising from a systems safety analysis that 

have been shown to have failure mode(s) 

associated with an ‘unsafe condition’ as 

defined in FAA’s memo 2003–112–15 ‘SFAR 

88—Mandatory Action Decision Criteria’. 

These are identified in Failure Conditions for 

which an unacceptable probability of ignition 

risk could exist if specific tasks and/or 

practices are not performed in accordance 

with the manufacturers’ requirements. 

This EASA Airworthiness Directive 

mandates the Fuel System Airworthiness 

Limitations, comprising maintenance/ 

inspection tasks and Critical Design Control 

Configuration Limitations (CDCCL) for the 

type of aircraft, that resulted from the design 

reviews and the JAA recommendation and 

EASA policy statement mentioned above. 

Revision History: PAD [proposed 

airworthiness directive] 06–018R1 has been 

issued to endorse comments received for 

PAD 06–018 and due to the change of the 

EASA policy statement on fuel tank safety on 

March 2006. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

12–18, With Revised Service Information 

Revision of Airplane Flight Manual (AFM) 

With Additional AFM References in Table 1 

of This AD 

(g) Within 30 days after July 21, 2006 (the 

effective date of AD 2006–12–18), revise the 

Limitations and Normal Procedures sections 

of the AFMs as specified in Table 1 of this 

AD to include the information in the 

applicable Shorts advance amendment 

bulletins as specified in Table 1 of this AD. 

The advance amendment bulletins address 

operation during icing conditions and fuel 

system failures. Thereafter, operate the 

airplane according to the limitations and 

procedures in the applicable advance 

amendment bulletin. 

Note 2: The requirements of paragraph (g) 

of this AD may be done by inserting a copy 

of the applicable advance amendment 

bulletin into the AFM. When the applicable 

advance amendment bulletin has been 

included in general revisions of the AFM, the 

general revisions may be inserted into the 

AFM and the advance amendment bulletin 

may be removed, provided the relevant 

information in the general revision is 

identical to that in the advance amendment 

bulletin. 

TABLE 1—AFM REVISIONS

Airplane Model— Shorts Advance Amendment Bulletin— AFM— 

SD3–30 airplanes ............................................... 1/2004, dated July 13, 2004 .............................. SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, 

SBH.3.8, and SB.3.9. 

SD3–60 airplanes ............................................... 1/2004, dated July 13, 2004 .............................. SB.4.3, SB.4.6, and SB.4.8. 

SD3–60 SHERPA airplanes ............................... 1/2004, dated July 13, 2004 .............................. SB.5.2 or 6.2. 

SD3–SHERPA airplanes ..................................... 1/2004, dated July 13, 2004 .............................. SB.6.2 or 5.2. 

Revision of Airworthiness Limitation (AWL) 

Section 

(h) Within 180 days after July 21, 2006: 

Revise the AWL section of the Instructions 

for Continued Airworthiness by 

incorporating airplane maintenance manual 

(AMM) Sections 5–20–01 and 5–20–02 as 

introduced by the Shorts temporary revisions 

(TR) specified in Table 2 of this AD into the 

AWL section of the AMMs for the airplane 

models specified in Table 2 of this AD, 

except as required by paragraph (j) of this 

AD. Thereafter, except as provided by 

paragraph (l)(1) of this AD, no alternative 

structural inspection intervals may be 

approved for the longitudinal skin joints in 

the fuselage shell. 

Note 3: The requirements of paragraph (h) 

of this AD may be done by inserting a copy 

of the applicable TR into the applicable 

AMM. When the TR has been included in 

general revisions of the AMM, the general 

revisions may be inserted in the AMM and 

the TR may be removed, provided the 

relevant information in the general revision 

is identical to that in the TR. 


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TABLE 2—AMM TEMPORARY REVISIONS

Airplane model— Temporary revision— Dated— AMM— 

SD3–30 airplanes ............................... TR330–AMM–13 ................................ June 21, 2004 .................................... SD3–30 AMM. 

SD3–30 airplanes ............................... TR330–AMM–14 ................................ June 21, 2004 .................................... SD3–30 AMM. 

SD3–60 airplanes ............................... TR360–AMM–33 ................................ July 27, 2004 ..................................... SD3–60 AMM. 

SD3–60 airplanes ............................... TR360–AMM–34 ................................ July 27, 2004 ..................................... SD3–60 AMM. 

SD3–60 SHERPA airplanes ............... TRSD360S–AMM–14 ........................ July 29, 2004 ..................................... SD3–60 SHERPA AMM. 

SD3–60 SHERPA airplanes ............... TRSD360S–AMM–15 ........................ July 29, 2004 ..................................... SD3–60 SHERPA AMM. 

SD3–SHERPA airplanes .................... TRSD3S–AMM–15 ............................ July 28, 2004 ..................................... SD3 SHERPA AMM. 

SD3–SHERPA airplanes .................... TRSD3S–AMM–16 ............................ July 28, 2004 ..................................... SD3 SHERPA AMM. 

Resistance Check, Inspection, and Jumper 

Installation 

(i) Within 180 days after July 21, 2006: 

Perform the insulation resistance check, 

general visual inspections, and bonding 

jumper wire installations; in accordance with 

Shorts Service Bulletin SD330–28–37, 

SD360–28–23, SD360 SHERPA–28–3, or SD3 

SHERPA–28–2; all dated June 2004; as 

applicable. If any defect or damage is 

discovered during any inspection or check 

required by this AD, before further flight, 

repair the defect or damage using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the Civil Aviation 

Authority (CAA) (or its delegated agent); or 

EASA (or its delegated agent). 

Note 4: 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.’’ 

New Requirements of This AD 

Revision of AWL Section: New Limitations 

and CDCCLs 

(j) Within 90 days after the effective date 

of this AD: Revise the AWL section of the 

Instructions for Continued Airworthiness by 

incorporating aircraft maintenance manual 

(AMM) Sections 5–20–01 and 5–20–02 as 

introduced by the Bombardier and Shorts 

temporary revisions (TRs) specified in Table 

3 of this AD into the AWL section of the 

AMMs for the airplane models specified in 

Table 3 of this AD. Doing this revision 

terminates the requirement to incorporate the 

temporary revisions specified in paragraph 

(h) of this AD. After doing this revision the 

temporary revisions required by paragraph 

(h) of this AD may be removed. 

TABLE 3—AMM TEMPORARY REVISIONS

Model— Temporary revision — Dated— To this AMM— 

SD3–30 airplanes ............. Shorts TR TR330–AMM–35 .................. June 6, 2006 .................... Shorts SD3–30 Maintenance Manual (MM). 

SD3–30 airplanes ............. Shorts TR TR330–AMM–36 .................. June 6, 2006 .................... Shorts SD3–30 MM. 

SD3–60 airplanes ............. Bombardier TR TR360–AMM–55 .......... November 11, 2005 ......... Bombardier SD3–60 AMM. 

SD3–60 airplanes ............. Bombardier TR TR360–AMM–56 .......... November 11, 2005 ......... Bombardier SD3–60 AMM. 

SD3–60 SHERPA airplanes.Shorts TR TRSD360S–AMM–35 .......... June 27, 2006 .................. Shorts SD3–60 Sherpa MM. 

SD3–60 SHERPA airplanes.Shorts TR TRSD360S–AMM–36 .......... June 27, 2006 .................. Shorts SD3–60 Sherpa MM. 

SD3–SHERPA airplanes ... Shorts TR TRSD3S–AMM–36 .............. June 19, 2006 .................. Shorts SD3–SHERPA MM. 

SD3–SHERPA airplanes ... Shorts TR TRSD3S–AMM–37 .............. June 19, 2006 .................. Shorts SD3–SHERPA MM. 

Note 5: The requirements of paragraph (j) 

of this AD may be done by inserting a copy 

of the applicable TR into the applicable 

AMM. When the TR has been included in 

general revisions of the AMM, the general 

revisions may be inserted in the AMM and 

the TR may be removed, provided the 

relevant information in the general revision 

is identical to that in the TR. 

(k) After accomplishing the actions 

specified in paragraph (j) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an alternative method of 

compliance (AMOC), in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

Explanation of CDCCL Requirements 

Note 6: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the AMM, as 

required by paragraph (h) or (j) of this AD, 

do not need to be reworked in accordance 

with the CDCCLs. However, once the AMM 

has been revised, future maintenance actions 

on these components must be done in 

accordance with the CDCCLs. 

FAA AD Differences 

Note 7: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(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 

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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

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


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
46868 Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(m) Refer to MCAI EASA Airworthiness 

Directive 2006–0198, dated July 11, 2006; 

Shorts Service Bulletins SD330–28–37, 

SD360–28–23, SD360 SHERPA–28–3, and 

SD3 SHERPA–28–2, all dated June 2004; and 

the service information listed in Tables 1, 2, 

and 3 of this AD; for related information. 

Issued in Renton, Washington, on July 26, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19172 Filed 8–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0402; Directorate 

Identifier 2007–NM–165–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes and 

Model 767 Airplanes Equipped With 

General Electric Model CF6–80C2 or 

CF6–80A Series Engines 

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 Model 747 airplanes and 

Model 767 airplanes. The original 

NPRM would have required revising the 

airplane flight manual (AFM) to advise 

the flightcrew to use certain procedures 

during descent in certain icing 

conditions. The original NPRM resulted 

from reports of several in-flight engine 

flameouts, including multiple dual 

engine flameout events and one total 

power loss event, in ice-crystal icing 

conditions. This action revises the 

original NPRM by revising the text of 

the proposed AFM revision. We are 

proposing this supplemental NPRM to 

ensure that the flightcrew has the proper 

procedures to follow in certain icing 

conditions. These certain icing 

conditions could cause a multiple 

engine flameout during flight with the 

potential inability to restart the engines, 

and consequent forced landing of the 

airplane. 

DATES: We must receive comments on 

this supplemental NPRM by August 30, 

2010. 

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. 

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 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: 

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. 

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–2008–0402; Directorate Identifier 

2007–NM–165–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 notice of proposed 

rulemaking (NPRM) (the ‘‘original 

NPRM’’) to amend 14 CFR part 39 to 

include an airworthiness directive (AD) 

that would apply to certain Model 747 

airplanes and Model 767 airplanes. That 

original NPRM was published in the 

Federal Register on April 7, 2008 (73 FR 

18721). That original NPRM proposed to 

require revising the airplane flight 

manual (AFM) to advise the flightcrew 

to use certain procedures during descent 

in certain icing conditions. 

Actions Since Original NPRM Was 

Issued 

Since we issued the original NPRM, 

we have received a report of another 

significant flameout event on a Model 

747 airplane. As a result of this latest 

event, Boeing has revised the AFM 

instructions to include the activation of 

wing anti-ice for those altitudes where 

wing anti-ice can be used while still 

ensuring that other systems that use 

bleed air are adequately supplied with 

bleed air. Therefore, we have revised the 

AFM text specified in paragraph (g) of 

this supplemental NPRM to include this 

new text. 

Other Relevant Rulemaking 

Related NPRM, Docket FAA–2008– 

0403, Directorate Identifier 2007–NM– 

166–AD (73 FR 18719, April 7, 2008), 

proposed to require similar actions for 

Model MD–11 and MD–11F airplanes, 

certified in any category, equipped with 

General Electric (GE) CF6–80C2 series 

engines. These airplanes have been 

determined to be subject to the 

identified unsafe condition addressed in 

this supplemental NPRM. 

Support for the Original NPRM 

The Air Line Pilots Association, 

International supports the intent and 

language of the original NPRM. The 

National Transportation Safety Board 

(NTSB), based on the success of similar 

AFM requirements to address this 

unsafe condition on Hawker Beechcraft 

Corporation Model 400, 400A, and 400T 

series airplanes, and Model MU–300 

airplanes, supports the adoption of the 

proposed requirements. 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1