Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 68543 

result of the transfer or disposition by a 

Federal Reserve Bank pursuant to a 

Transfer Message that the Federal 

Reserve Bank reasonably believes to be 

genuine. 

(b) The obligation of the Banks and 

the Office of Finance to make payments 

of interest and principal with respect to 

Book-entry consolidated obligations is 

discharged at the time payment in the 

appropriate amount is made as follows: 

(1) Interest on Book-entry 

consolidated obligations is either 

credited by a Federal Reserve Bank to a 

Funds Account maintained at the 

Federal Reserve Bank or otherwise paid 

as directed by the Participant. 

(2) Book-entry consolidated 

obligations are paid, either at maturity 

or upon redemption, in accordance with 

their terms by a Federal Reserve Bank 

withdrawing the securities from the 

Participant’s Securities Account in 

which they are maintained and by either 

crediting the amount of the proceeds, 

including both principal and interest, 

where applicable, to a Funds Account at 

the Federal Reserve Bank or otherwise 

paying such principal and interest as 

directed by the Participant. No action by 

the Participant is required in connection 

with the payment of a Book-entry 

consolidated obligation, unless 

otherwise expressly required. 

§ 1270.16 Authority of Federal Reserve 

Banks. 

(a) Each Federal Reserve Bank is 

hereby authorized as fiscal agent of the 

Office of Finance: To perform functions 

with respect to the issuance of Bookentry consolidated obligations, in 

accordance with the terms of the 

applicable offering notice and with 

procedures established by the Office of 

Finance; to service and maintain Bookentry consolidated obligations in 

accounts established for such purposes; 

to make payments of principal, interest 

and redemption premium (if any), as 

directed by the Office of Finance; to 

effect transfer of Book-entry 

consolidated obligations between 

Participants’ Securities Accounts as 

directed by the Participants; and to 

perform such other duties as fiscal agent 

as may be requested by the Office of 

Finance. 

(b) Each Federal Reserve Bank may 

issue Operating Circulars not 

inconsistent with this part 1270, 

governing the details of its handling of 

Book-entry consolidated obligations, 

Security Entitlements, and the operation 

of the Book-entry system under this part 

1270. 

§ 1270.17 Liability of Banks, FHFA, Office 

of Finance and Federal Reserve Banks. 

The Banks, the Finance Board, the 

Office of Finance and the Federal 

Reserve Banks may rely on the 

information provided in a tender, 

transaction request form, other 

transaction documentation, or Transfer 

Message, and are not required to verify 

the information. Neither the Banks, 

FHFA, the Director, the Office of 

Finance, the United States, nor the 

Federal Reserve Banks shall be liable for 

any action taken in accordance with the 

information set out in a tender, 

transaction request form, other 

transaction documentation, or Transfer 

Message, or evidence submitted in 

support thereof. 

§ 1270.18 Additional requirements; notice 

of attachment for Book-entry consolidated 

obligations. 

(a) Additional requirements. In any 

case or any class of cases arising under 

the regulations in this part 1270, the 

Office of Finance may require such 

additional evidence and a bond of 

indemnity, with or without surety, as 

may in its judgment, or in the judgment 

of the Banks or FHFA, be necessary for 

the protection of the interests of the 

Banks, FHFA, the Office of Finance or 

the United States. 

(b) Notice of attachment. The interest 

of a debtor in a Security Entitlement 

may be reached by a creditor only by 

legal process upon the Securities 

Intermediary with whom the debtor’s 

securities account is maintained, except 

where a Security Entitlement is 

maintained in the name of a secured 

party, in which case the debtor’s interest 

may be reached by legal process upon 

the secured party. The regulations in 

this part 1270 do not purport to 

establish whether a Federal Reserve 

Bank is required to honor an order or 

other notice of attachment in any 

particular case or class of cases. 

§ 1270.19 Reference to certain Department 

of Treasury commentary and 

determinations. 

Notwithstanding provisions in 

§ 1270.6 regarding Department of 

Treasury regulations set forth in 31 CFR 

part 357: 

(a) The Department of Treasury 

TRADES Commentary (31 CFR part 357, 

appendix B) addressing the Department 

of Treasury regulations governing bookentry procedure for Treasury Securities 

is hereby referenced, so far as applicable 

and as necessarily modified to relate to 

Book-entry consolidated obligations, as 

an interpretive aid to this subpart D of 

this part. 

(b) Determinations of the Department 

of Treasury regarding whether a State 

shall be considered to have adopted 

Revised Article 8 for purposes of 31 CFR 

part 357, as published in the Federal 

Register or otherwise, shall also apply 

to this subpart D of this part. 

§ 1270.20 Obligations of United States with 

respect to consolidated obligations. 

Consolidated obligations are not 

obligations of the United States and are 

not guaranteed by the United States. 

Dated: November 3, 2010. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

[FR Doc. 2010–28178 Filed 11–5–10; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1101; Directorate 

Identifier 2009–CE–013–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 150, 152, 

170, 172, 175, 177, 180, 182, 185, 188, 

190, 195, 206, 207, 210, T303, 336, and 

337 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 87–20–03 

R2, which applies to certain Cessna 

Aircraft Company (Cessna) 150, 152, 

170, 172, 175, 177, 180, 182, 185, 188, 

190, 195, 206, 207, 210, T303, 336, and 

337 series airplanes. AD 87–20–03 R2 

currently requires repetitive inspections 

and replacement of parts, if necessary, 

of the seat rail and seat rail holes; seat 

pin engagement; seat rollers, washers, 

and axle bolts or bushings; wall 

thickness of roller housing and the tang; 

and lock pin springs. Since we issued 

AD 87–20–03 R2, we have added steps 

to the inspection procedures, added 

revised figures, and clarified some of the 

existing steps. Consequently, this 

proposed AD would retain all of the 

actions from the previous AD and add 

steps to the inspection procedures in the 

previous AD. We are proposing this AD 

to prevent seat slippage or the seat roller 

housing from departing the seat rail, 

which may consequently cause the 

pilot/copilot to be unable to reach all 

the controls. This failure could lead to 


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68544 Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 

the pilot/copilot losing control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 23, 

2010. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• 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. 

FOR FURTHER INFORMATION CONTACT: Gary 

Park, Aerospace Engineer, ACE–118W, 

Wichita Aircraft Certification Office 

(ACO), 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; telephone: (316) 

946–4123; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include the docket 

number, ‘‘FAA–2010–1101; Directorate 

Identifier 2009–CE–013–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light 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 

concerning this proposed AD. 

Discussion 

Reports of seats slipping on the rails 

on Cessna airplanes caused us to issue 

AD 87–20–03 R2, Amendment 39–6669. 

AD 87–20–03 R2 currently requires 

repetitive inspections and replacement 

of parts if necessary of the seat rail and 

seat rail holes; seat pin engagement; seat 

rollers, washers, and axle bolts or 

bushings; wall thickness of roller 

housing and the tang; and lock pin 

springs on Cessna 150, 152, 170, 172, 

175, 177, 180, 182, 185, 188, 190, 195, 

206, 207, 210, T303, 336, and 337 series 

airplanes. 

We have in the last 20 years received 

several reports of accidents, some fatal, 

for Cessna airplanes where the primary 

latch pin for the pilot/copilot seat is not 

properly engaged in the seat rail/track. 

There have also been incidents where 

the seat roller housing has departed the 

seat rail. Consequently, we have added 

steps to the inspection procedures, 

added revised figures, and clarified 

some of the existing steps. 

This condition, if not corrected, could 

result in seat slippage or the seat roller 

housing departing from the seat rail, 

which may consequently cause the 

pilot/copilot to be unable to reach all 

the controls. This failure could lead to 

the pilot/copilot losing control of the 

airplane. 

FAA’s Determination and Requirements 

of the Proposed AD 

We are proposing this AD because we 

evaluated all information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This proposed AD would 

supersede AD 87–20–03 R2 with a new 

AD that would retain all of the actions 

from the previous AD and add steps to 

the inspection procedures in the 

previous AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 36,000 airplanes in the 

U.S. registry. 

The estimated total cost on U.S. 

operators includes the cumulative costs 

associated with AD 87–20–03 R2. The 

required actions of this proposed AD are 

the same as in AD 87–20–03 R2 with the 

exception of some added steps to the 

inspection, which do not increase workhours. The increased estimated cost of 

this AD is due to increased labor cost 

and parts cost from 1987 when AD 87– 

20–03 R2 was issued. 

We estimate the following costs to do 

the proposed inspections: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

1 work-hour × $85 per hour = $85 ..................................................................... Not applicable ......................... $85 $3,060,000 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of airplanes 

that may need this replacement: 

Labor cost Parts cost Total cost per 

airplane 

Seat rail: 2 work-hours × $85 per hour = $170 per rail ................................................................................. $225 per rail ............ $395 

Seat roller kit: 2 work-hours per seat (less per leg) × $85 per hour = $170 ................................................ 110 .......................... 280 

Miscellaneous parts, such as seat rollers, washers, bushings, bolts, lock pin springs, etc.: 1 work-hour 

per seat × $85 per hour = $85.

15 ............................ 100 

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. 


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Regulatory Findings 

We have 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 that the 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. 

Examining the AD Docket 

You may examine the AD docket that 

contains the proposed AD, the 

regulatory evaluation, any comments 

received, and other information 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 Docket Office (telephone 

(800) 647–5527) is located at the street 

address stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

87–20–03 R2, Amendment 39–6669, and 

adding the following new AD: 

Cessna Aircraft Company: Docket No. FAA– 

2010–1101; Directorate Identifier 2009– 

CE–013–AD. 

Comments Due Date 

(a) We must receive comments on this 

airworthiness directive (AD) action by 

December 23, 2010. 

Affected ADs 

(b) This AD supersedes AD 87–20–03 R2, 

Amendment 39–6669. 

Applicability 

(c) This AD applies to all serial numbers 

of the following Cessna Aircraft Company 

(Cessna) Models that are certificated in any 

category: 

Models 

150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, F150F, F150G, F150H, F150J, F150K,

F150L, F150M, FA150K, FA150L, FA150M, FRA150L, and FRA150M 

152, A152, F152, and FA152 

170, 170A, and 170B 

172, 172A, 172B, 172C, 172D, 172E, 172F (USAF T–41A), 172G, 172H (USAF T–41A), 172I, 172K, 172L, 172M, 172N, 172P, 172Q, 172RG,

F172D, F172E, F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P, FR172E, FR172F, FR172G, FR172H, FR172J, FR172K, 

P172D, R172E (USAF T-41B) (USAF T–41C and D), R172F (USAF T–41D), R172G (USAF T–41C or D), R172H (USAF T–41D), R172J, and 

R172K 

175, 175A, 175B, and 175C 

177, 177A, 177B, 177RG, and F177RG 

180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, and 180K 

182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, F182P, F182Q, FR182, R182,

T182, and TR182 

185, 185A, 185B, 185C, 185D, 185E, A185E, and A185F 

188, 188A, A188, A188A, 188B, A188B, and T188C 

190 

195, 195A, and 195B 

206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, TU206A, TU206B, TU206C, TU206D, 

TU206E, TU206F, TU206G, U206, U206A,U206B, U206C, U206D, U206E, U206F, and U206G 

207, 207A, T207, and T207A 

210, 210–5 (205), 210–5A (205A), 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, 210N, 210R, P210N, P210R, 

T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N, and T210R 

T303 

336 

337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, F337E, F337F, F337G, F337H, FT337E, FT337F, FT337GP, FT337HP, M337B, 

P337H, T337B, T337C, T337D, T337E, T337F, T337G, T337H, and T337H–SP 

Unsafe Condition 

(d) This AD results from reports of seats 

slipping on the rails where the primary latch 

pin for the pilot/copilot seat is not properly 

engaged in the seat rail/track and reports of 

the seat roller housing departing the seat rail. 

We are issuing this AD to prevent seat 

slippage or the seat roller housing from 

departing the seat rail, which may 

consequently cause the pilot/copilot to be 

unable to reach all the controls. This failure 

could lead to the pilot/copilot losing control 

of the airplane. 

Compliance 

(e) For all airplanes, to address the unsafe 

condition described in paragraph (d) of this 

AD, you must do the following actions on the 

seat rails; seat rollers, washers, and axle bolts 

or bushings; seat roller housings and the 

tangs; and lock pin springs, unless already 

done, initially within the next 100 hours 

time-in-service (TIS) after the last inspection 

done following AD 87–20–03 R2 or within 

the next 12 calendar months after the 

effective date of this AD, whichever occurs 

first. Repetitively thereafter do the actions at 

intervals not to exceed every 100 hours TIS 

or every 12 months, whichever occurs first: 

(1) Visually inspect the pilot and copilot 

seat rails for dirt and debris that may prevent 

engagement of the seat locking pins. Before 

further flight, after any inspection where dirt 

or debris is found, remove the dirt or debris 

found. 

(2) Lift up the forward edge of each seat to 

eliminate vertical play of the seat locking pin 


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68546 Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 

in the engagement hole, and from this 

position, inspect the depth of engagement of 

each seat locking pin (see figure 2). If the rail 

is worn, this depth is measured from the 

worn surface, not the manufactured surface. 

(i) If engagement of any of the seat locking 

pins measures less than 0.15 of an inch, 

before further flight, replace or repair any 

seat components necessary to achieve a seat 

pin engagement of a minimum of 0.15 of an 

inch. 

(ii) Repair or replacement of necessary seat 

components does not terminate the repetitive 

actions required in paragraph (e) of this AD. 

(3) Remove the seat from the seat rail. 

(i) Remove the seat stops. 

(ii) Disengage seat belt/shoulder harness 

from the seat, if necessary. 

(iii) Raise vertical adjusting seats to 

maximum height. 

(iv) Hold seat latches disengaged and slide 

the seat forward and aft to disengage rollers. 

(v) Lift the seat out of the airplane. 

(4) Inspect the diameter of each seat 

locking pin engagement hole in the pilot and 

copilot seat rails for excessive wear. Due to 

wear on the rail surface at the hole opening, 

we allow this measurement 0.020 of an inch 

below the surface of the rail. You must take 

this measurement somewhere between the 

surface of the rail or no more than 0.020 of 

an inch below the surface of the rail. 

(i) If the diameter of any of the holes is 0.42 

of an inch or more (see figure 1), before 

further flight, replace the rail. 

(ii) Rail replacement does not terminate the 

repetitive actions required in paragraph (e) of 

this AD. 

BILLING CODE 4910–13–P 

(5) Visually inspect the seat rollers for flat 

spots and inspect the rollers and washers for 

binding. Assure all rollers and washers, 

which are meant to rotate, turn freely on their 

axles (or bushings if installed). 

(i) Before further flight, replace any rollers 

with flat spots and any worn washers. 

(ii) Before further flight, remove and clean 

the parts if there is any binding between the 

bores of the rollers, washers, or axles. 

(iii) Do not lubricate the rollers, washers, 

or axles because the lubricant will attract 

dust and other particles that may cause 

binding. 

(6) Inspect the thickness of the tang (see 

figure 2 and figure 3). Due to wear of the tang 

chafing against the seat rail, measure the tang 

thickness where the tang inner edges contact 

the seat rail. 

(i) If the tang thickness measures less than 

0.05 of an inch, before further flight replace 

the roller housing. 

(ii) Replacement of the roller housing does 

not terminate the repetitive actions required 

in paragraph (e) of this AD. 


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Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 68547 

(7) Inspect the inner edges of the tangs. 

Due to wear or deformation of the tangs, 

measure the distance from one tang inner 

edge to the other tang inner edge 

(see figure 4). 

(i) The maximum distance allowed 

between tang edges is 0.44 inches. If the 

distance between tang inner edges measures 

0.44 of an inch or more, before further flight, 

replace the roller housing. 

(ii) The minimum measurement allowed 

for the remaining tang is 0.130 inches 

remaining on either of the tangs, from the 

inner edge of the tang to the bend of the 

roller housing. If the measurement is less 

than 0.130 inches on either of the tangs, 

before further flight, replace the roller 

housing. 

(iii) Replacement of the roller housing does 

not terminate the repetitive actions required 

in paragraph (e) of this AD. 

(8) Inspect the springs that keep the lock 

pins in position in the rail holes for positive 

engagement action. Before further flight, 

replace any spring that does not provide 

positive engagement. 

(9) Visually inspect the seat rails for cracks. 

(i) If there are seat rail cracks that exceed 

the crack criteria in figure 5, before further 

flight, replace the seat rail. 

(ii) Replacement of the seat rail does not 

terminate the repetitive actions required in 

paragraph (e) of this AD. 

BILLING CODE 4910–13–P 


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68548 Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 

(10) Reinstall the seat on the seat rail. 

(i) Lift the seat into the airplane and place 

on the seat rail. 

(ii) Hold seat latch disengaged and slide 

the seat aft and then forward to re-engage 

rollers. 

(iii) Lower vertical adjusting seats to a 

comfortable height. 

(iv) Reattach seat belt/shoulder harness to 

the seat, if previously attached to the seat. 

(v) Reinstall the seat stops. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Wichita 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. Send information to ATTN: Gary 

Park, Aerospace Engineer, ACE–118W, 

Wichita Aircraft Certification Office (ACO), 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4123; 

fax: (316) 946–4107. 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. 

(h) AMOCs approved for AD 87–20–03 R2 

are approved for this AD. 

Related Information 

(i) To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, or on 

the Internet at http://www.regulations.gov. 

Issued in Kansas City, Missouri on 

November 1, 2010. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–28158 Filed 11–5–10; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1045; Directorate 

Identifier 2010–NM–101–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. 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: 

One case of elevator servo-control 

disconnection has been experienced on an 

aeroplane of the A320 family. Investigation 

has revealed that the failure occurred at the 

servo-control rod eye-end. 

Further to this finding, additional 

inspections have revealed cracking at the 

same location on a number of other servocontrol rod eye-ends. In several cases, both 

actuators of the same elevator surface were 

affected. The root cause of the cracking has 

not yet been determined and tests are 

ongoing. 

A dual servo-control disconnection on the 

same elevator could result in an uncontrolled 

surface, the elevator surface being neither 

actuated nor damped, which could lead to 

reduced control of the aeroplane. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 


emcdonald on DSK2BSOYB1PROD with PROPOSALSEP08NO10.043</GPH>