40230 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 

Avenue, SW., Renton, Washington; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 11, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–13979 Filed 7–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28747; Directorate 

Identifier 2006–NM–275–AD; Amendment 

39–15137; AD 2007–15–08] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

ATP Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all BAE Systems 

(Operations) Limited Model ATP 

airplanes. The existing AD currently 

requires revising the Airworthiness 

Limitations Section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA) to incorporate life 

limits for certain items and inspections 

to detect fatigue cracking in certain 

structures; to incorporate new 

inspections to detect fatigue cracking of 

certain significant structural items 

(SSIs); and to revise life limits for 

certain equipment and various 

components. This new AD requires 

revising the ALS of the ICA to include 

revised requirements. This AD results 

from the determination that additional 

and revised inspections of the fuselage 

are needed. We are issuing this AD to 

detect and correct fatigue cracking of 

certain structural elements, which could 

result in reduced structural integrity of 

the airplane and consequent rapid 

decompression of the airplane. 

DATES: This AD becomes effective 

August 8, 2007. 

On September 21, 2006 (71 FR 52418, 

September 6, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of BAE 

Systems (Operations) Limited Service 

Bulletin ATP–51–002, dated December 

20, 2005. 

We must receive comments on this 

AD by September 24, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go 

to http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• 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. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room W12–140 on 

the ground floor of the West Building, 

1200 New Jersey Avenue, SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

Contact British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 23, 2006, we issued AD 

2006–18–09, amendment 39–14748 (71 

FR 52418, September 6, 2006), for all 

BAE Systems (Operations) Limited 

Model ATP airplanes. That AD requires 

revising the Airworthiness Limitations 

Section (ALS) of the Instructions for 

Continued Airworthiness (ICA) to 

incorporate life limits for certain items 

and inspections to detect fatigue 

cracking in certain structures; to 

incorporate new inspections to detect 

fatigue cracking of certain significant 

structural items (SSIs); and to revise life 

limits for certain equipment and various 

components. That AD resulted from 

manufacturer review of fatigue test 

results that identified additional and 

revised inspections of the fuselage that 

are necessary in order to ensure the 

continued structural integrity of the 

airplane. We issued that AD to detect 

and correct fatigue cracking of certain 

structural elements, which could result 

in reduced structural integrity of the 

airplane and consequent rapid 

decompression of the airplane. The 

actions specified in that AD correspond 

to British airworthiness directive G–

2004–0020, dated August 25, 2004, and 

European Aviation Safety Agency 

(EASA) airworthiness directive 2006–

0090, dated April 20, 2006. 

Actions Since Existing AD Was Issued 

Since we issued AD 2006–18–09, the 

Civil Aviation Authority (CAA), which 

is the airworthiness authority for the 

United Kingdom, notified us that an 

unsafe condition may exist on all BAE 

Systems (Operations) Limited Model 

ATP airplanes. The CAA advises that 

the certification requirements for 

damage tolerant and safe life structure 

are given in Chapter 5 of the BAE ATP 

aircraft maintenance manual (AMM). 

The CAA has identified the need to 

revise these requirements to add and 

change inspections of the fuselage. The 

revisions primarily recognize the 

introduction of Modification 

JDM60138N, which installs an energyabsorbing stop to aircraft fitted with the 

large freight door. Failure to adopt the 

latest revision of Chapter 5 of the AMM 

could result in fatigue cracking of 

certain structural elements remaining 

undetected, which could result in 

reduced structural integrity of the 

airplane and consequent rapid 

decompression of the airplane. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued revisions to Section 05–10–

12, ‘‘Mandatory Life Limitations 

(Airframe—Structures),’’ dated January 

15, 2007; Section 05–10–15, 

‘‘Mandatory Life Limitations 

(Powerplant/Engine/APU—Structures),’’

dated January 15, 2007; and Section 05–

10–17, ‘‘Structurally Significant Items 

(SSIs),’’ dated January 15, 2007; of the 

BAE Systems (Operations) Limited ATP 

AMM; which refer to additional 

chapters of the AMM. Those revised 

sections of the AMM include mandatory 

life limitations for the airframe and 

power plant/engine; and structural 

inspections of the fuselage, engine, 

horizontal stabilizer, and wing bottom 

surface. The revised sections also 

describe new inspections and 

compliance times for inspection and 

replacement actions. Accomplishment 

of those actions will prevent the onset 

of fatigue cracking of certain structural 

elements of the airplane. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The CAA mandated the 

service information and issued British 

airworthiness directive G–2005–0031, 


pwalker on PROD1PC71 with RULES
Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 40231 

dated October 20, 2005 (which 

supersedes British airworthiness 

directive G–2004–0020, dated August 

25, 2004), to ensure the continued 

airworthiness of these airplanes in the 

United Kingdom. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in the United Kingdom and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAA has 

kept the FAA informed of the situation 

described above. We have examined the 

CAA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

This AD supersedes AD 2006–18–09 

and retains the requirements of the 

existing AD. This AD also requires 

revising the ALS of the ICA to include 

new and revised inspections. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work 

hours 

Average labor 

rate per hour 

Cost per 

airplane 

ALS Revisions ....................................................................................................................................... 1 $80 $80 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–28747; Directorate Identifier 

2006–NM–275–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located on the 

ground floor of the West Building at the 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 


pwalker on PROD1PC71 with RULES
40232 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14748 (71 

FR 52418, September 6, 2006) and by 

adding the following new airworthiness 

directive (AD): 

2007–15–08 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

15137. Docket No. FAA–2007–28747; 

Directorate Identifier 2006–NM–275–AD. 

Effective Date 

(a) This AD becomes effective August 8, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2006–18–09. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model ATP airplanes, 

certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new and revised 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 (m) 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. 

Unsafe Condition 

(d) This AD results from the determination 

that additional and revised inspections of the 

fuselage are needed. We are issuing this AD 

to detect and correct fatigue cracking of 

certain structural elements, which could 

result in reduced structural integrity of the 

airplane and consequent rapid 

decompression of the airplane. 

Compliance 

(e) 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–

18–09 

Airworthiness Limitations Revision 

Specified in AD 2000–26–10 

(f) Within 30 days after February 7, 2001 

(the effective date of AD 2000–26–10, 

amendment 39–12060, which was 

superseded by AD 2005–19–03), revise the 

Airworthiness Limitations section (ALS) of 

the Instructions for Continued Airworthiness 

according to a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. One 

approved method is by incorporating Section 

05–00–00, dated August 15, 1997, of the 

British Aerospace ATP Aircraft Maintenance 

Manual (AMM), dated October 15, 1999, into 

the ALS. This section references other 

chapters of the AMM. The applicable 

revision level of the referenced chapters is 

that in effect on February 7, 2001. Doing the 

revision specified in paragraph (g) of this AD 

replaces Chapters 27, 32, 53, and 54 listed in 

Section 05–10–11 and Chapters 52, 53, 54, 

55, and 57 listed in Section 05–10–17 that are 

in effect on February 7, 2001, with Chapters 

27, 32, 53, and 54 listed in Section 05–10–

11, ‘‘Mandatory Life Limitations (Airframe)’’; 

and Chapters 52, 53, 54, 55, and 57 listed in 

Section 05–10–17, ‘‘Structurally Significant 

Items (SSIs)’’; both dated July 15, 2004; of the 

British Aerospace ATP AMM. Doing the 

revision specified in paragraph (k) of this AD 

replaces Sections 05–10–12, 05–10–15, and 

05–10–17 with the corresponding sections 

specified in paragraph (k) of this AD. 

Airworthiness Limitations Specified in AD 

2005–19–03 

(g) Within 30 days after September 28, 

2005 (the effective date of AD 2005–19–03, 

amendment 39–14268, which was 

superseded by AD 2006–18–09), revise the 

ALS of the Instructions for Continued 

Airworthiness according to a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. One approved method is 

by incorporating the tasks for Chapters 27, 

32, 53, and 54 listed in Section 05–10–11, 

‘‘Mandatory Life Limitations (Airframe)’’; 

and the tasks for Chapters 52, 53, 54, 55, and 

57 listed in Section 05–10–17, ‘‘Structurally 

Significant Items (SSIs)’’; both dated July 15, 

2004; of the British Aerospace ATP AMM; 

into the ALS. These chapters replace the 

corresponding chapters in Section 05–00–00, 

dated August 15, 1997, of the British 

Aerospace ATP AMM as specified in 

paragraph (f) of this AD. Doing the revision 

specified in paragraph (h) of this AD replaces 

certain Chapter 52 and 53 tasks listed in 

Section 05–10–17, ‘‘Structurally Significant 

Items (SSIs),’’ dated July 15, 2004, of the 

British Aerospace ATP AMM, with the 

corresponding Chapter 52 and 53 tasks listed 

in BAE Systems (Operations) Limited Service 

Bulletin ATP–51–002, dated December 20, 

2005. Doing the revision specified in 

paragraph (k) of this AD replaces Chapters 

52, 53, 54, 55, and 57 listed in Section 05–

10–17 with the corresponding Section 05–

10–17 specified in paragraph (k) of this AD. 

New and Revised Airworthiness Limitations 

in AD 2006–18–09 

(h) Within 30 days after September 21, 

2006 (the effective date of AD 2006–18–09), 

revise the ALS of the Instructions for 

Continued Airworthiness by incorporating 

the new and revised tasks for Chapters 52 

and 53 as specified in BAE Systems 

(Operations) Limited Service Bulletin ATP–

51–002, dated December 20, 2005, into the 

ALS. The revised Chapter 52 and 53 tasks 

replace the corresponding Chapter 52 and 53 

tasks in Section 05–10–17, ‘‘Structurally 

Significant Items (SSIs),’’ dated July 15, 2004, 

of the British Aerospace ATP AMM, as 

specified in paragraph (g) of this AD. 

(i) Except as provided by paragraph (m) of 

this AD: After the actions specified in 

paragraphs (f), (g), and (h) of this AD have 

been accomplished, no alternative 

inspections or inspection intervals may be 

approved for the structural elements 

specified in the documents listed in 

paragraphs (f), (g), and (h) of this AD. 

No Reporting Required 

(j) Although BAE Systems (Operations) 

Limited Service Bulletin ATP–51–002, dated 

December 20, 2005, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

New Requirements of This AD 

Revised Limitations 

(k) Within 30 days after the effective date 

of this AD, revise the ALS of the Instructions 

for Continued Airworthiness according to a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA. One approved 

method is by incorporating Section 05–10–

12, ‘‘Mandatory Life Limitations (Airframe—

Structures),’’ dated January 15, 2007; Section 

05–10–15, ‘‘Mandatory Life Limitations 

(Powerplant/Engine/APU—Structures),’’

dated January 15, 2007; and Section 05–10–

17, ‘‘Structurally Significant Items (SSIs),’’

dated January 15, 2007; of the BAE Systems 

(Operations) Limited ATP AMM; into the 

ALS. The revised sections replace the 

corresponding sections specified in 

paragraphs (f) and (g) of this AD. 

(l) Except as provided by paragraph (m) of 

this AD: After the action specified in 

paragraph (k) of this AD has been 

accomplished, no alternative inspections or 

inspection intervals may be approved for the 

structural elements specified in the 

documents listed in paragraph (k) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 


pwalker on PROD1PC71 with RULES
Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 40233 

Related Information 

(n) British airworthiness directive G–2005–

0031, dated October 20, 2005, and European 

Aviation Safety Agency (EASA) 

airworthiness directive 2006–0090, dated 

April 20, 2006, also address the subject of 

this AD. 

Material Incorporated by Reference 

(o) You must use BAE Systems 

(Operations) Limited Service Bulletin ATP–

51–002, dated December 20, 2005, to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. On 

September 21, 2006 (71 FR 52418, September 

6, 2006), the Director of the Federal Register 

approved the incorporation by reference of 

this document. Contact British Aerospace 

Regional Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 20171, for 

a copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on July 15, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–14134 Filed 7–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27431 Directorate 

Identifier 2007;–016–AD; Amendment 39–

15132; AD 2007–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Stemme 

GmbH & Co. KG Model S10–V and 

S10-VT Powered Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Service experience showed that the 

connection screw of the propeller blade 

follower type 10AP–VM may break and the 

main part of the blade follower can be lost 

in flight. This condition, if not corrected, 

could lead to high vibration during powered 

flight and consequently result in decreased 

control of the aircraft. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 28, 2007. 

On August 28, 2007, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Greg 

Davison, Glider Program Manager, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 23, 2007 (72 FR 

20072). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Service experience showed that the 

connection screw of the propeller blade 

follower type 10AP–VM may break and the 

main part of the blade follower can be lost 

in flight. This condition, if not corrected, 

could lead to high vibration during powered 

flight and consequently result in decreased 

control of the aircraft. 

Stemme has developed a new blade 

follower, Model 10AP–VP, which is 

reinforced on the shaft and has an Allen head 

screw installed instead of a slotted screw. For 

the reason stated above, this Emergency 

Airworthiness Directive (EAD) requires the 

replacement of the blade follower type 

10AP–VM with the new type 10AP–VP. 

This EAD has been revised to correct the 

TCDS reference and the applicability 

statement. No separate TC was issued for the 

affected propellers. These propellers are part 

of the aircraft type design. 

Paragraph (4) of the ‘‘Compliance’’ section 

of this EAD has been corrected. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required 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 AD. 

Costs of Compliance 

We estimate that this AD will affect 

53 products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $117 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $18,921 or 

$357 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. 


pwalker on PROD1PC71 with RULES