Federal Register / Vol. 60, No. 51 / Thursday, March 16, 1995 / Proposed Rules 14235

that may not include separating the terminal

fitting from the spar chord to detect cracking

and corrosion of all eight wing terminal-tospar chord joints, in accordance with a

method approved by the Manager, Seattle

ACO. To be considered acceptable, the

equivalent inspection(s) must include, at a

minimum, the criteria specified in

paragraphs (b)(2)(i), (b)(2)(ii), and (b)(2)(iii) of

this AD.

(i) The inspection must include removal of

all 64 bolts that join the eight wing terminals

to the eight spar chords; and

(ii) The inspection must adequately detect

cracking of the spar chord, and corrosion

between the terminal fitting and the spar

chord; and

(iii) The inspection must include a visual

inspection to detect corrosion of the

attachment bolts; and a high frequency eddy

current, and boroscope inspection at 10

power magnification, of the bolt holes

common to the spar chord-to-wing terminal

interface.

(c) If any cracking and/or corrosion is

detected during any of the inspections

required by paragraphs (a) and (b) of this AD,

prior to further flight, repair in accordance

with a method approved by the Manager,

Seattle ACO.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on March 9,

1995.

Neil D. Schalekamp,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–6321 Filed 3–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–13–AD]

Airworthiness Directives; Fairchild

Aircraft SA226 and SA227 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Fairchild Aircraft SA226 and SA227

series airplanes that utilize a direct

current (DC) generator. The proposed

action would require relocating the lefthand (LH) and right-hand (RH) essential

bus current limiters (225 amp) to the

battery bus (main bus tie). A safety

recommendation received by the

Federal Aviation Administration (FAA)

that details potential electrical failure

problems on Fairchild SA226 and

SA227 series airplanes prompted the

proposed action. The actions specified

by the proposed AD are intended to

prevent failure of the LH or RH essential

bus when engine failure results in a

blown generator current limiter, which

could result in loss of airplane electrical

power.

DATES: Comments must be received on

or before June 2, 1995.

ADDRESSES: Submit comments in

triplicate to the FAA, Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 95–CE–13–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Fairchild Aircraft, P.O. Box 790490, San

Antonio, Texas 78279–0490; telephone

(210) 824–9421. This information also

may be examined at the Rules Docket at

the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

George R. Hash, Aerospace Engineer,

FAA, Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone (817) 222–5134;

facsimile (817) 222–5959.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 95–CE–13–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 95–CE–13–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Discussion

The FAA has received a safety

recommendation that details potential

electrical failure problems on Fairchild

SA226 and SA227 series airplanes.

Flight simulation revealed that electrical

power loss could occur on the affected

airplanes because of failure of the LH

essential bus. Switching delays between

the left and right side electrical systems

result in left generator motor action,

which could then cause the left side

current limiter to open. This would

result in failure of the left essential bus,

which will result in loss of alternating

current (AC) power to the primary

attitude indicator and the lighting for

the standby attitude indicator.

Failure of either engine will result in

the loss of the essential bus for that side

if the motoring action of the generator

causes the current limiter to open. This

condition, if not detected and corrected,

could result in loss of airplane electrical

power including loss of attitude and

landing gear power.

Fairchild has issued Service Bulletin

(SB) 226–24–034, SB 227–24–015, and

SB CC7–24–002, all Issued: September

29, 1994. These service bulletins

reference a modification that relocates

the RH and LH essential bus current

limiters (225 amp) to the battery bus

(main bus tie). Fairchild Aircraft

Engineering Kit Drawing 27K82376,

‘‘Current Limiter Rebussing Kit,’’

contains the specific procedures for

incorporating this modification on the

affected airplanes.

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that AD action

should be taken to prevent the situation

described above from occurring.
14236 Federal Register / Vol. 60, No. 51 / Thursday, March 16, 1995 / Proposed Rules

Since an unsafe condition has been

identified that is likely to exist or

develop in other Fairchild Aircraft

SA226 and SA227 series airplanes of the

same type design that utilize a direct

current (DC) generator, the proposed AD

would require relocating the LH and RH

essential bus current limiters (225 amp)

to the battery bus (main bus tie).

Accomplishment of the proposed

modification would be in accordance

with Fairchild Aircraft Engineering Kit

Drawing 27K82376, ‘‘Current Limiter

Rebussing Kit,’’ as referenced in

Fairchild SB 226–24–034, SB 227–24–

015, and SB CC7–24–002, all Issued:

September 29, 1994.

The FAA estimates that 622 airplanes

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 4 workhours per airplane

to accomplish the proposed action, and

that the average labor rate is

approximately $60 an hour. Parts cost

approximately $98 per airplane. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $210,236 ($338 per

airplane). This figure is based on the

assumption that no affected airplane

owner/operator has incorporated the

proposed modification. Fairchild

Aircraft has informed the FAA that parts

have not been distributed to any owner/

operator of the affected airplanes.

The regulations proposed herein

would not have substantial direct effects

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. Therefore,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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. A copy of the draft

regulatory evaluation prepared for this

action has been placed in the Rules

Docket. A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new AD to read as follows:

Fairchild Aircraft: Docket No. 95–CE–13–

AD.

Applicability: The following model and

serial number airplanes that utilize a direct

current (DC) generator, certificated in any

category.

Models Serial Nos.

SA226–T, SA226–AT,

SA226–TC, and SA226–

T(B).

All.

SA227–AC, SA227–AT,

SA227–BC, and SA227–

TT.

1 through 733.

SA227–CC and SA227–

DC.

784, and 790

through 883.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any aircraft from the

applicability of this AD.

Compliance: Required within the next

2,000 hours time-in-service after the effective

date of this AD, unless already accomplished.

To prevent failure of the left hand (LH) and

right hand (RH) essential bus when engine

failure results in a blown generator current

limiter, which could result in loss of airplane

electrical power, accomplish the following:

(a) Relocate the LH and RH essential bus

current limiters (225 amp) to the battery bus

(main bus tie) in accordance with Fairchild

Aircraft Engineering Kit Drawing 27K82376,

‘‘Current Limiter Rebussing Kit,’’ as

referenced in the following service bulletins

(SB):

SB Date Models affected

226–24–034 ..................................... September 29, 1994 ........................................... All affected SA226 models.

227–24–05 ....................................... September 29, 1994 ........................................... SA227–AD, SA227-AT, SA227–BC, and SA227-TT.

CC7–24–002 .................................... September 29, 1994 ........................................... SA227–CC and SA227–DC.

(b) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Fort Worth

Airplane Certification Office (ACO), FAA,

2601 Meacham Boulevard, Fort Worth, Texas

76193–0150. The request shall be forwarded

through an appropriate FAA Maintenance

Inspector, who may add comments and then

send it to the Manager, Fort Worth ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth ACO.

(d) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to Fairchild Aircraft,

P.O. Box 790490, San Antonio, Texas 78279–

0490; or may examine this document at the

FAA, Central Region, Office of the Assistant

Chief Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on March

10, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–6471 Filed 3–15–95; 8:45 am]

BILLING CODE 4910–13–U